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Fuselage
Skin and Bonded Doubler
Category - Airframe
Effective Date - 04/24/2000
Recurring - No
Supersedes - N/A
Superseded by - N/A
Amendment 39-11629.
Docket 99-NM-73-AD.
Applicability:
All Model 727 series airplanes, certificated in any category.
Note 1: This AD applies
to each airplane identified in the preceding applicability provision,
regardless of whether it has been 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 (c) 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 fatigue cracking of the fuselage skin and bonded doubler area
above the forward entry doorway, which could result in reduced structural
integrity and consequent loss of cabin pressurization, accomplish the
following:
Detailed Visual Inspection
(a) Prior to the accumulation of 60,000 total flight cycles, or within
3,000 flight cycles after the effective date of this AD, whichever occurs
later: Perform a one-time detailed visual inspection of the fuselage skin
and bonded doubler area above the forward entry doorway to detect fatigue
cracking or the existence of a previous repair, in accordance with Boeing
Service Bulletin 727-53-0186, Revision 1, dated May 21, 1992.
Corrective Action
(1) If no crack or
repair is detected, prior to further flight, perform the preventive modification
in accordance with the service bulletin. No further action is required
by this AD.
(2) If any crack but
no repair is detected, prior to further flight, accomplish the actions
required by paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii), as applicable.
(i) If any crack is less than or equal to 2.5 inches, perform the full-sized
repair doubler in accordance with Boeing Service Bulletin 727-53-0186,
Revision 1, dated May 21, 1992. Accomplishment of this action constitutes
terminating action for the requirements of this AD.
(ii) If any crack exceeds 2.5 inches, repair in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office (ACO),
FAA, Transport Airplane Directorate; or in accordance with data meeting
the type certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative (DER) who has been authorized by
the Manager, Seattle ACO, to make such findings. For a repair method to
be approved by the Manager, Seattle ACO, or the Boeing DER, as required
by this paragraph, the approval letter must specifically reference this
AD. (iii) If any crack in the bear strap is detected, repair in accordance
with a method approved by the Manager, Seattle ACO; or in accordance with
data meeting the type certification basis of the airplane approved by
a Boeing Company DER who has been authorized by the Manager, Seattle ACO,
to make such findings. For a repair method to be approved by the Manager,
Seattle ACO, or the Boeing DER, as required by this paragraph, the approval
letter must specifically reference this AD.
(3) If any repair
is found, accomplish paragraph (a)(3)(i), (a)(3)(ii), or (a)(3)(iii),
of this AD, as applicable.
(i) If a full-sized repair doubler is found, as specified by Boeing Service
Bulletin 727-53-0186, dated April 27, 1989, or Revision 1, dated May 21,
1992, and any crack is less than or equal to 2.5 inches, no further action
is required by this AD. (ii) If a half-sized repair doubler is found,
as specified by Boeing Service Bulletin 727-53-0186, dated April 27, 1989,
or Revision 1, dated May 21, 1992, and any crack is less than or equal
to 2.5 inches and is not in the bear strap: Prior to further flight, perform
the full-sized repair doubler in accordance with Boeing Service Bulletin
727-53-0186, Revision 1, dated May 21, 1992. No further action is required
by this AD.
(iii) If a half-sized or full-sized repair doubler is found, as specified
by the service bulletin, and any crack exceeds 2.5 inches or is located
in the bear strap: Prior to further flight, repair in accordance with
a method approved by the Manager, Seattle ACO or in accordance with data
meeting the type certification basis of the airplane approved by a Boeing
Company DER who has been authorized by the Manager, Seattle ACO, to make
such findings. For a repair method to be approved by the Manager, Seattle
ACO, or the Boeing DER, as required by this paragraph, the approval letter
must specifically reference this AD.
Note 2: For the purposes
of this AD, a detailed visual inspection is defined as: "An intensive
visual examination of a specific structural area, system, installation,
or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity
deemed appropriate by the inspector. Inspection aids such as mirrors,
magnifying lenses, etc. may be used. Surface cleaning and elaborate access
procedures may be required." Terminating Action for AD 94-05-04 (b) Accomplishment
of the requirements of this AD constitutes terminating action for the
requirements of paragraph (a) of AD 94-05-04, amendment 39-8842 (which
are required to be accomplished in accordance with Appendices A.3, B.3,
and C.3 of Boeing Document Number D6-54860, "Aging Airplane Service Bulletin
Structural Modification and Inspection Program--Model 727," Revision G,
dated March 5, 1993), with respect to the modification specified in Boeing
Service Bulletin 727-53-0186, dated April 27, 1989. All other service
bulletins referenced in Boeing Document Number D6-54860 still apply.
Alternative Methods
of Compliance
(c) 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 ACO. 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 3: Information concerning
the existence of approved alternative methods of compliance with this
AD, if any, may be obtained from the Seattle ACO.
Special Flight Permits
(d) Special flight permits may be issued in accordance with Sec. 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. Incorporation by Reference
(e) Except as provided by paragraphs (a)(2)(ii), (a)(2)(iii), and (a)(3)(iii)
of this AD, the actions shall be done in accordance with Boeing Service
Bulletin 727-53-0186, Revision 1, dated May 21, 1992. 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.
(f) This amendment becomes effective on April 24, 2000.
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 (425) 227-2774;
fax (425) 227-1181. Issued in Renton, Washington, on March 8, 2000. Donald
L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
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