[Federal Register: March 9, 2004 (Volume 69, Number 46)]
[Rules and Regulations]
[Page 10917-10919]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09mr04-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-49-AD; Amendment 39-13511; AD 2004-05-16]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
[[Page 10918]]
applicable to certain Boeing Model 767-200 and -300 series airplanes,
that requires repetitive inspections of the aft pressure bulkhead web,
and corrective action, if necessary. This action is necessary to detect
and correct fatigue cracks in the aft pressure bulkhead web, which
could result in uncontrolled rapid decompression. This action is
intended to address the identified unsafe condition.
DATES: Effective April 13, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 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 Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Airframe Branch,
ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98055-4056; telephone (425) 917-6441; 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 all Boeing Model 767-200, -300,
and -300F series airplanes was published in the Federal Register on
October 6, 2003 (68 FR 57639). That action proposed to require
repetitive inspections of the aft pressure bulkhead web, and corrective
action, 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 comments received.
Concur With Proposed AD
One commenter has reviewed the proposed AD and concurs with the
proposed inspections and corrective action.
Add Provision for Flight Cycles With Cabin Differential Pressure Less
Than 2.0 psi
One commenter requests that a provision be added allowing flight
cycles to not be counted if cabin differential pressure was below 2.0
pounds per square inch (psi), provided that cabin pressure records be
maintained for each airplane, and that no fleet averaging of cabin
pressure is allowed. The commenter notes that there is a provision in
Boeing Alert Service Bulletin 767-53A0087, dated October 21, 1999,
which is the source of service information for this AD. In the
``General Notes'' of the Accomplishment Instructions of the service
bulletin, paragraph 6. specifies that ``flight-cycles, as defined
herein, need not be counted if cabin differential pressure was below
2.0 psi.''
We do not agree with the commenter's request to add a provision for
flight cycles with cabin differential pressure less than 2.0 psi. Cabin
differential pressure of 2.0 psi or less is not typical of normal
operation of the affected airplanes. We do not consider it appropriate
to include various provisions in an AD applicable to unique uses of an
affected airplane. We have determined that mitigating factors, such as
total number of low pressure cycles, could best be evaluated through
requests for alternative methods of compliance, as provided by
paragraph (e) of this AD. In addition, we have clarified paragraphs (a)
and (b) of this AD by referring to the ``Work Instructions'' of the
service bulletin instead of the ``Accomplishment Instructions.''
Change Effectivity and Revise Affected Models
One commenter requests the applicability be changed to line numbers
1 through 423 inclusive and that Model -300F series airplanes be
removed from the list of affected models. The commenter states that AD
2003-18-10, amendment 39-13301 (68 FR 53503, September 11, 2003),
mandates the current revision of Section 9 of the Maintenance Planning
Data document, which contains inspection item number 53-80-I01A.
Inspection item number 53-80-I01A is the same as the proposed actions
for line numbers 424 and on. This would cause duplicate requirements
for the same actions, causing confusion for operators as to what
inspections to accomplish and how to comply with both ADs.
The FAA agrees with the commenter's request. For line numbers 424
and on, the Airworthiness Limitations for Boeing Model 767 series
airplanes are currently in effect and AD 2003-18-10 adequately mandates
the proposed inspections and corrective action. We have changed the
applicability to line numbers 1 through 423 inclusive and removed Model
-300F series airplanes from the list of affected models. Because of the
new applicability, we also removed Group 3 and Group 4 from Table 1 of
this AD, revised paragraph (b) of this AD, and changed the number of
affected airplanes in the ``Cost Impact'' paragraph of the AD.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 406 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 182 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 14 work
hours per airplane to accomplish the required inspection, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be $165,620, or
$910 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
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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:
2004-05-16 Boeing: Amendment 39-13511. Docket 2003-NM-49-AD.
Applicability: Model 767-200 and -300 series airplanes, line
numbers 1 through 423 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracks in the aft pressure
bulkhead web, which could result in uncontrolled rapid
decompression, accomplish the following:
Initial and Repetitive Inspections
(a) Do high frequency eddy current inspections of the aft
pressure bulkhead web, per the Work Instructions of Boeing Alert
Service Bulletin 767-53A0087, dated October 21, 1999; at the later
of the applicable ``Threshold'' and ``Grace Period'' times specified
in Table 1 of this AD. Table 1 is as follows:
Table 1.--Compliance Times for Inspection
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Compliance times--
For-- -------------------------------------------------------------------------
Threshold-- Grace period--
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(1) Group 1 airplanes as identified in Prior to the accumulation of Within 18 months or within 3,000 flights
the service bulletin. 37,500 total flight cycles. after the effective date of this AD,
whichever comes first
(2) Group 2 airplanes as identified in Prior to the accumulation of Within 18 months or within 3,000 flights
the service bulletin. 50,000 total flight cycles. after the effective date of this AD,
whichever comes first
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(b) If no crack is found during any inspection required by
paragraph (a) of this AD, repeat the high frequency eddy current
inspections thereafter at intervals not to exceed 6,000 flight
cycles, per the Work Instructions of Boeing Alert Service Bulletin
767-53A0087, dated October 21, 1999.
Corrective Actions
(c) If any crack is found during any inspection required by
paragraph (a) or (b) of this AD and Boeing Alert Service Bulletin
767-53A0087, dated October 21, 1999, specifies to contact Boeing for
repair: Before further flight, repair per a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or per
data meeting the type certification basis of the airplane approved
by a Boeing Company Designated Engineering Representative who has
been authorized by the Manager, Seattle ACO, to make such findings.
For a repair method to be approved, the approval must specifically
reference this AD.
Previously Installed Repairs
(d) If previously installed repairs are installed in the
inspection area, and Boeing Alert Service Bulletin 767-53A0087,
dated October 21, 1999, specifies to contact Boeing for inspection
details, an alternative method of compliance must be approved as
required by sections 39.15, 39.17, and 39.19 of the Code of Federal
Regulations (14 CFR 39.15, 39.17, 39.19).
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, Seattle ACO,
FAA, is authorized to approve alternative methods of compliance for
this AD.
Incorporation by Reference
(f) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 767-53A0087,
dated October 21, 1999. 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 Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
Effective Date
(g) This amendment becomes effective on April 13, 2004.
Issued in Renton, Washington, on February 25, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-4922 Filed 3-8-04; 8:45 am]
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