Elevator Control Tab

Category - Airframe
Effective Date - 04/22/1996
Recurring - Yes
Supersedes - 84-22-02 & 87-24-03
Superseded by - N/A
Amendment 39-9542. Docket 94-NM-179-AD.
Supersedes AD 84-22-02, amendment 39-4951; and AD 87-24-03, amendment 39-5769.

Applicability: Model 727 series airplanes, line numbers 1 through 1832 inclusive; certificated in any category.

Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (j) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent excessive free play of the elevator control tab and possible tab flutter, accomplish the following:

(a) For airplanes on which the modification or repair described in Boeing Service Bulletin 727-55-0085, dated August 31, 1984 (specified as terminating action in AD 84-22-02, amendment 39-4951), has not been accomplished and the repetitive inspections required by AD 84-22-02 have not been initiated: Prior to the accumulation of 8,000 total flight hours since date of manufacture, or within 300 flight hours after the effective date of this AD, whichever occurs later, perform a visual inspection to detect cracks and loose hinge brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, in accordance with Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Then accomplish the follow-on actions (i.e., repetitive inspections, stop-drilling, modification) in accordance with that service bulletin, at the times specified as follows.

Note 2: AD 84-22-02 pertains to the one-piece elevator rear spar.

(1) Repeat the visual inspection thereafter at intervals not to exceed 1,600 flight hours.

(2) If any crack is detected and stop-drilled as a result of any inspection required by this paragraph, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(b) For airplanes on which the modification or repair described in Boeing Service Bulletin 727-55-0085, dated August 31, 1984 (specified as terminating action in AD 84-22-02, amendment 39-4951), has not been accomplished and the repetitive inspections required by AD 84-22-02 have been initiated: Accomplish either paragraph (b)(1) or (b)(2) of this AD, as applicable.

(1) If no crack has been detected as a result of inspections required by AD 84-22-02: Within 1,600 flight hours after the last inspection required by that AD, perform a visual inspection to detect cracks and loose brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, in accordance with the Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplish follow-on actions (i.e., repetitive inspection, stop-drilling, modification) in accordance with that service bulletin, at the times specified as follows:

(i) Repeat the visual inspection thereafter at intervals not to exceed 1,600 flight hours.

(ii) If any crack is detected and stop-drilled as a result of any inspection required by this paragraph, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(2) If any crack has been stop-drilled in accordance with AD 84-22-02, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(c) For airplanes on which the modification or repair described in Boeing Service Bulletin 727-55-0085, dated August 31, 1984 (specified as terminating action in AD 84-22-02, amendment 39-4951), has been accomplished: Within 4,000 flight hours after the effective date of this AD, perform a visual inspection to detect cracks and loose hinge brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, in accordance with Boeing Service Bulletin 727-55-0089, dated June 29, 1995.

Accomplish follow-on actions (i.e., repetitive inspections, stop-drilling, modification) in accordance with that service bulletin, at the times specified as follows:

(1) Repeat the visual inspection thereafter at intervals not to exceed 4,000 flight hours.

(2) If any crack is detected and stop-drilled as a result of any inspection required by this paragraph, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(d) For airplanes on which the modification or repair described in Boeing Service Bulletin 727-55-087, dated June 20, 1986 (specified as terminating action in AD 87-24-03, amendment 39-5769), has not been accomplished and the repetitive inspections required by AD 87-24-03 have not been initiated: Accomplish the requirements of paragraph (d)(1) of this AD at the earliest of the times specified in paragraph (d)(2).

Note 3: AD 87-24-03 pertains to the two-piece elevator rear spar.

(1) Perform a visual inspection to detect cracks and loose hinge brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, at the earliest of the times specified in paragraph (d)(2) of this AD, and in accordance with Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplish follow-on actions (i.e., repetitive inspection, stop-drilling, modification) in accordance with that service bulletin, at the times specified as follows:

(i) Repeat the visual inspection thereafter at intervals not to exceed 4,000 flight hours.

(ii) If any crack is detected and stop-drilled as a result of any inspection required by this paragraph, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(2) Accomplish the initial visual inspection required by paragraph (d)(1) of this AD at the earliest of the following times:

(i) Prior to the accumulation of 27,000 total flight hours since date of manufacture, or within 4,000 flight hours after December 24, 1987 (the effective date of 87-24-03, amendment 39-5769), whichever occurs later; or

(ii) Prior to the accumulation of 12,000 total flight hours since date of manufacture, or within 4,000 flight hours after the effective date of this AD, whichever occurs later; or

(iii) Prior to the accumulation of 27,300 total flight hours since date of manufacture, or within 300 flight hours after the effective date of this AD, whichever occurs later.

(e) For airplanes on which the modification or repair described in Boeing Service Bulletin 727-55-087, dated June 20, 1986 (specified as terminating action in AD 87-24-03, amendment 39-5769), has not been accomplished and the repetitive inspections required by AD 87-24-03 have been initiated: Accomplish either paragraph (e)(1) or (e)(2) of this AD, as applicable.

(1) If no crack has been detected as a result of inspections required by AD 87-24-03: Within 4,000 flight hours after the last inspection required by that AD, perform a visual inspection to detect cracks and loose brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, in accordance with Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplish follow-on actions (i.e., repetitive inspection, stop-drilling, modification) in accordance with that service bulletin, at the times specified as follows:

(i) Repeat the visual inspection thereafter at intervals not to exceed 4,000 flight hours.

(ii) If any crack is detected and stop-drilled as a result of any inspection required by paragraph (e)(1) of this AD, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(2) If any crack has been detected and stop-drilled in accordance with AD 87-24-03, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(f) For airplanes on which the modification or repair described in Boeing Service Bulletin 727-55-087, dated June 20, 1986 (specified as terminating action in AD 87-24-03, amendment 39-5769), has been accomplished: Within 4,000 flight hours after the effective date of this AD, perform a visual inspection to detect cracks and loose hinge brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, in accordance with Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplish follow-on actions (i.e., repetitive inspection, stop-drilling, modification) in accordance with the service bulletin, at the times specified as follows:

(1) Repeat the visual inspection thereafter at intervals not to exceed 4,000 flight hours.

(2) If any crack is detected and stop-drilled as a result of any inspection required by this paragraph, accomplish the requirements of paragraph (g) of this AD at the times specified in that paragraph.

(g) If any crack is detected and stop-drilled in accordance with paragraph (a)(2), (b)(1)(ii), (b)(2), (c)(2), (d)(1)(ii), (e)(1)(ii), (e)(2), or (f)(2) of this AD, accomplish the following:

(1) Within 1,600 flight hours after stop-drilling, perform a visual inspection to detect cracks and loose hinge brackets of the elevator rear spar in the area along the upper and lower edges at the shear plate, and accomplish follow-on actions (i.e., stop-drilling, modification) in accordance with the service bulletin. If any crack growth is detected after stop-drilling, prior to further flight, modify the elevator rear spar in accordance with Part II of the Accomplishment Instructions of Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of this AD.

(2) Within 3,200 flight hours after stop-drilling, modify the elevator rear spar in accordance with Part II of the Accomplishment Instructions of Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of this AD.

(h) Modification of the elevator rear spar in accordance with Part II of the Accomplishment Instructions of Boeing Service Bulletin 727-55-0089, dated June 29, 1995, constitutes terminating action for the requirements of this AD.

(i) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(j) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO.

Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.

(k) The actions shall be done in accordance with Boeing Service Bulletin 727-55-0089, dated June 29, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(l) This amendment becomes effective on April 22, 1996.

FOR FURTHER INFORMATION CONTACT:

Walter Sippel, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206) 227-2774; fax (206) 227-1181.