[Federal Register: September 8, 2004 (Volume 69, Number 173)]
[Rules and Regulations]
[Page 54211-54213]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08se04-6]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-131-AD; Amendment 39-13786; AD 2004-18-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727, 727C, 727-100, -100C,
and -200 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Boeing Model 727, 727C, 727-100, -100C, and -200
series airplanes. This amendment requires an inspection of the forward
trunnion attach fittings of the main landing gear (MLG), inspections of
the attach fitting holes of the forward trunnion attach fittings if
necessary, replacement of the forward trunnion attach fittings if
necessary, and corrective actions if necessary. This action is
necessary to detect and correct cracks and corrosion on the attach
fitting holes of the forward trunnion attach fittings of the MLG, which
could result in the collapse of the MLG. This action is intended to
address the identified unsafe condition.
DATES: Effective October 13, 2004.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of October 13, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207. 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 National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go to:
http://www.archives.gov/federal--register/code--of--federal--
regulations/ibr--locations.html.
FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6456; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Boeing Model 727, 727C,
727-100, -100C, and -200 series airplanes was published in the Federal
Register on June 16, 2004 (69 FR 33587). That action proposed to
require an inspection of the forward trunnion attach fittings of the
main landing gear, inspections of the attach fitting holes of the
forward trunnion attach fittings if necessary, replacement of the
forward trunnion attach fittings if necessary, and corrective actions
if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 523 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 309 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 1 work
hour per airplane to accomplish the required inspection, and that the
average labor rate is $65 per work hour. Based on these figures, the
[[Page 54212]]
cost impact of the AD on U.S. operators is estimated to be $20,085, or
$65 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2004-18-08 Boeing: Amendment 39-13786. Docket 2003-NM-131-AD.
Applicability: Model 727, 727C, 727-100, -100C, and -200 series
airplanes, line numbers 1 through 887 inclusive; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracks and corrosion on the attach fitting
holes of the forward trunnion attach fittings of the main landing
gear (MLG), which could result in the collapse of the MLG,
accomplish the following:
Service Bulletin References
(a) The term ``service bulletin,'' as used in this AD, means
Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March
20, 2003.
Initial Inspection
(b) Perform an inspection of the forward trunnion attach
fittings of the MLG to determine the part number (P/N) of the attach
fitting, in accordance with ``Part 1'' of the Accomplishment
Instructions of the service bulletin, at the latest of the times
specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD:
(1) Prior to airplanes reaching 240 months old since the date of
issuance of the original Airworthiness Certificate or the date of
issuance of the original Export Certificate of Airworthiness; or
(2) Within 18 months after the effective date of this AD; or
(3) Within 120 months after the last inspection/rework/repair of
the attach fitting per Boeing Service Bulletin 727-57A0132, dated
June 28, 1974, Revision 1, dated October 31, 1975, or Revision 2,
dated April 24, 1981; or Boeing Alert Service Bulletin 727-57A0132,
Revision 3, dated March 20, 2003.
Corrective Actions
(c) If, during the inspection required by paragraph (b) of this
AD, both attach fittings are found to have P/N 65-19296-9, -10, -13,
or -14; P/N 65-99909-1724 or -1727; P/N 65-19296U13 or P/N 65-
19296U14 (attach fitting made of 7075-T73511 or 7050-T7451
aluminum); no further action is required by this paragraph.
(d) If, during the inspection required by paragraph (b) of this
AD, any attach fitting is found to have P/N 65-19296-1 through -8
inclusive (attach fitting made of 7079-T6 aluminum): Before further
flight, perform the actions in paragraphs (d)(1) and (d)(2) of this
AD, as applicable.
(1) Do detailed and high frequency eddy current inspections of
the attach fitting holes for cracks and corrosion, repair any crack
or corrosion found, and rework the attach fitting holes, in
accordance with Figures 4 and 5 of the service bulletin, except as
provided by paragraph (d)(2) of this AD.
(2) If the attach fitting hole cannot be reworked or repaired in
accordance with Figures 4 and 5 of the service bulletin: Before
further flight, replace the attach fitting with a new attach fitting
that has P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -
1727, P/N 65-19296U13, or P/N 65-19296U14, in accordance with
paragraph 7 of ``Part II'' of the Accomplishment Instructions of the
service bulletin. Accomplishment of this replacement is terminating
action for that fitting.
Terminating Action
(e) Within 120 months after the effective date of this AD,
replace attach fittings that have P/N 65-19296-1 through -8 (attach
fittings made of 7079-T6 aluminum) with new attach fittings that
have P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727,
P/N 65-19296U13, or P/N 65-19296U14 (attach fittings made of 7075-
T73511 or 7050-T7451 aluminum), in accordance with paragraph 7 of
``Part II'' of the Accomplishment Instructions of the service
bulletin. Replacement of all attach fittings made of 7079-T6
aluminum with new attach fittings made of 7075-T73511 or 7050-T7451
aluminum terminates the requirements of paragraph (d) of this AD.
Parts Installation
(f) As of the effective date of this AD, no person shall
install, on any airplane, an attach fitting, P/N 65-19296-1, -2, -3,
-4, -5, -6, -7, or -8 (attach fitting made of 7079-T6 aluminum),
unless it has been inspected/reworked/repaired in accordance with
paragraph (d) of this AD.
Alternative Methods of Compliance
(g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.
(2) An AMOC that provides an acceptable level of safety may be
used for any rework/repair required by this AD, if it is approved by
a Boeing Company Designated Engineering Representative (DER) who has
been authorized by the Manager, Seattle ACO, to make such findings.
For a rework/repair method to be approved, the approval must
specifically reference this AD.
Incorporation by Reference
(h) The actions shall be done in accordance with Boeing Alert
Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003. 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 Airplanes, 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 National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: http://
www.archives.gov/federal--register/code--of--federal--regulations/
ibr--locations.html.
Effective Date
(i) This amendment becomes effective on October 13, 2004.
[[Page 54213]]
Issued in Renton, Washington, on August 26, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20205 Filed 9-7-04; 8:45 am]
BILLING CODE 4910-13-P