[Federal Register Volume 64, Number 106 (Thursday, June 3, 1999)]
[Rules and Regulations]
[Pages 29777-29778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-12829]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 64, No. 106 / Thursday, June 3, 1999 / Rules
and Regulations
[[Page 29777]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-110-AD; Amendment 39-11177; AD 99-08-05 R1]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9 and C-9
(Military) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
-----------------------------------------------------------------------
SUMMARY: This amendment corrects information in an existing
airworthiness directive (AD), applicable to certain McDonnell Douglas
Model DC-9 and C-9 (military) series airplanes, that currently requires
repetitive inspections to detect fatigue cracking of the fuselage
frames and longerons 16R and 17R above the forward lower cargo door;
repair, if necessary; and modification of the fuselage frames and
longerons, if necessary, and follow-on repetitive inspections to detect
fatigue cracking of the skin adjacent to the modification. That AD was
prompted by numerous instances of fatigue cracking of the fuselage
frames and longerons. The actions specified by that AD are intended to
prevent fatigue cracking of the fuselage frames and longerons 16R and
17R, which could result in reduced structural integrity of the
airplane. This amendment corrects an erroneous reference to a certain
volume of the Supplemental Inspection Document.
DATES: Effective May 12, 1999.
The incorporation by reference of McDonnell Douglas Service
Bulletin DC9-53-267, dated October 20, 1997, was approved previously by
the Director of the Federal Register as of May 12, 1999 (64 FR 16805,
April 7, 1999).
ADDRESSES: The service information referenced in this AD may be
obtained from The Boeing Commercial Aircraft Group, Douglas Products
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Technical Publications Business Administration, Dept. C1-L51
(2-60). This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport
Airplane Directorate, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5324; fax (562)
627-5210.
SUPPLEMENTARY INFORMATION: On March 30, 1999, the Federal Aviation
Administration (FAA) issued AD 99-08-05, amendment 39-11110 (64 FR
16805, April 7, 1999), which applies to certain McDonnell Douglas Model
DC-9 and C-9 (military) series airplanes. That AD requires repetitive
inspections to detect fatigue cracking of the fuselage frames and
longerons 16R and 17R above the forward lower cargo door; repair, if
necessary; and modification of the fuselage frames and longerons, if
necessary, and follow-on repetitive inspections to detect fatigue
cracking of the skin adjacent to the modification. That AD was prompted
by numerous instances of fatigue cracking of the fuselage frames and
longerons. The actions required by that AD are intended to prevent
fatigue cracking of the fuselage frames and longerons 16R and 17R,
which could result in reduced structural integrity of the airplane.
AD 99-08-05 contains an error in paragraph (d) of the AD. That
paragraph contains a reference to McDonnell Douglas Model DC-9
Supplemental Inspection Document, Report No. L26-008, Section 2 of
Volume III-95, dated September 1995. The correct reference is McDonnell
Douglas Model DC-9 Supplemental Inspection Document, Report No. L26-
008, Section 2 of Volume I, Revision 5, dated July 1997.
Action is taken herein to correct the error in AD 99-08-05 and to
correctly add the AD as an amendment to Sec. 39.13 of the Federal
Aviation Regulations (14 CFR 39.13).
The final rule is being reprinted in its entirety for the
convenience of affected operators. The effective date remains May 12,
1999.
Since this action only corrects an error, it has no adverse
economic impact and imposes no additional burden on any person.
Therefore, notice and public procedures hereon are unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Correction
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-11110 (64 FR
16805, April 7, 1999), and by adding a new airworthiness directive
(AD), amendment 39-11177, to read as follows:
99-08-05 R1 McDonnell Douglas: Amendment 39-11177. Docket 98-NM-
110-AD. Revises AD 99-08-05, Amendment 39-11110.
Applicability: Model DC-9 and C-9 (military) series airplanes,
as listed in McDonnell Douglas Service Bulletin DC9-53-267, dated
October 20, 1997; 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 (e) 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
[[Page 29778]]
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 frames and longerons
16R and 17R, which could result in reduced structural integrity of
the airplane, accomplish the following:
(a) Prior to the accumulation of 30,000 total landings, or
within 3,000 landings after the effective date of this AD, whichever
occurs later, perform a visual inspection to detect fatigue cracking
of the fuselage frames and longerons 16R and 17R above the forward
lower cargo door, in accordance with paragraph 3.B.1. of the
Accomplishment Instructions of McDonnell Douglas Service Bulletin
DC9-53-267, dated October 20, 1997.
(b) Condition 1. If no cracking is detected during the
inspection required by paragraph (a) of this AD, accomplish the
requirements of either paragraph (b)(1) or (b)(2) of this AD, in
accordance with McDonnell Douglas Service Bulletin DC9-53-267, dated
October 20, 1997.
(1) Option 1. Repeat the visual inspection required by paragraph
(a) of this AD thereafter at intervals not to exceed 19,000
landings. Or
(2) Option 2. Prior to further flight, modify the fuselage
frames and longerons 16R and 17R. Prior to the accumulation of
19,000 landings after accomplishment of the modification, perform
the visual inspection specified in paragraph 3.B.1.D. of the
Accomplishment Instructions of the service bulletin to detect
fatigue cracking of the skin adjacent to the modification.
(i) If no cracking is detected, repeat the visual inspection
thereafter at intervals not to exceed 19,000 landings.
(ii) If any cracking is detected, prior to further flight,
repair in accordance with a method approved by the Manager, Los
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate.
(c) Condition 2. If any cracking is detected during the
inspection required by paragraph (a) of this AD, prior to further
flight, repair the cracked area and modify the fuselage frames and
longerons 16R and 17R; in accordance with McDonnell Douglas Service
Bulletin DC9-53-267, dated October 20, 1997. Prior to the
accumulation of 19,000 landings after accomplishment of the
modification, perform the visual inspection specified in paragraph
3.B.1.D.(5) of the Accomplishment Instructions of the service
bulletin to detect fatigue cracking of the skin adjacent to the
modification, in accordance with the service bulletin.
(1) If no cracking is detected, repeat the visual inspection
thereafter at intervals not to exceed 19,000 landings.
(2) If any cracking is detected, prior to further flight, repair
in accordance with a method approved by the Manager, Los Angeles
ACO.
(d) Accomplishment of the inspections required by this AD
constitutes terminating action for the inspections of Principal
Structural Element 53.09.055A (reference McDonnell Douglas Model DC-
9 Supplemental Inspection Document, Report No. L26-008, Section 2 of
Volume I, Revision 5, dated July 1997), as required by AD 96-13-03,
amendment 39-9671.
Alternative Methods of Compliance
(e) 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, Los Angeles ACO. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Los Angeles ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(f) 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.
Incorporation by Reference
(g) Except as provided by paragraphs (b)(2)(ii) and (c)(2) of
this AD, the actions shall be done in accordance with McDonnell
Douglas Service Bulletin DC9-53-267, dated October 20, 1997. The
incorporation by reference of this document was approved previously
by the Director of the Federal Register as of May 12, 1999 (64 FR
16805, April 7, 1999). Copies may be obtained from Boeing Commercial
Aircraft Group, Douglas Products Division, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention: Technical Publications
Business Administration, Dept. C1-L51 (2-60). Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane
Directorate, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(h) The effective date of this amendment remains May 12, 1999.
Issued in Renton, Washington, on May 14, 1999.
Donald E. Gonder,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-12829 Filed 6-2-99; 8:45 am]
BILLING CODE 4910-13-P