[Federal Register Volume 76, Number 37 (Thursday, February 24, 2011)]
[Proposed Rules]
[Pages 10288-10291]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-4200]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0044; Directorate Identifier 2010-NM-059-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 767-200, -300,
-300F, and -400ER Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to The Boeing Company Model 767-200, -300, and -300F
series airplanes. The existing AD currently requires inspections to
detect cracking or corrosion of the fail-safe straps between the side
fitting of the rear spar bulkhead at body station 955 and the skin; and
follow-on and corrective actions. Since we issued that AD, we have
received additional reports of cracks in 51 fail-safe straps on 41
airplanes; we have also received a report of a crack found in the ``T''
fitting that connects the fail-safe strap to the outboard edge of the
pressure deck. This proposed AD would expand the applicability, and
would add an inspection for cracking in the fail-safe strap, and repair
or replacement if necessary. We are proposing this AD to detect and
correct fatigue cracking or corrosion of the fail-safe straps and the
``T'' fittings, which could result in cracking of adjacent structure
and consequent reduced structural integrity of the fuselage.
DATES: We must receive comments on this proposed AD by April 11, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; e-mail [email protected]; Internet
https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: 425-917-
6577; fax: 425-917-6590; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0044;
Directorate Identifier 2010-NM-059-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On September 26, 2005, we issued AD 2004-19-06 R1, amendment 39-
14313 (70 FR 58000, October 5, 2005), for certain Model 767-200, -300,
and -300F series airplanes. That AD requires inspections to detect
cracking or corrosion of the fail-safe straps between the side fitting
of the rear spar bulkhead at body station (BS) 955 and the skin; and
follow-on/corrective actions. That AD resulted from reports of cracked
and/or corroded fail-safe straps at BS 955 on Model 767-200 series
airplanes. We issued that AD to detect and correct fatigue cracking or
corrosion of the fail-safe straps, which could result in cracking of
adjacent structure and consequent reduced structural integrity of the
fuselage.
Actions Since Existing AD Was Issued
Since we issued AD 2004-19-06 R1, we have received additional
reports of cracks in 51 fail-safe straps on 41 airplanes. There were 42
fail-safe straps repaired, and 9 were not repairable and were replaced.
Fail-safe straps were repaired on 33 airplanes with total accumulated
flight cycles ranging from 39,886 to 89,236. Fail-safe straps were
replaced on 9 airplanes with flight cycles ranging from 12,565 to
31,809, and flight hours ranging from 48,704 to 93,212. In addition, 4
fail-safe straps on 4 airplanes with total accumulated flight cycles
ranging from 12,540 to 23,987 and flight hours ranging from 37,634 to
74,823 were replaced due to corrosion damage.
One report was received of a crack found in the ``T'' fitting that
connects the fail-safe strap and the pressure deck. The cracked ``T''
fitting was found at
[[Page 10289]]
13,449 total accumulated flight cycles and 74,008 flight hours, and was
located at the lower of the 3 fastener holes common to the fail-safe
strap.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 767-53A0100, Revision 1,
dated August 11, 2006; and Revision 2, dated January 15, 2010. Revision
1 of this service bulletin both adds certain Model 767-400ER airplanes
to the Effectivity, and removes other airplanes from the Effectivity,
of Boeing Alert Service Bulletin 767-53A0100, dated September 26, 2002
(which is identified as the appropriate source of service information
for accomplishing the actions specified in the existing AD). Revision 1
also adds procedures for an ultrasonic inspection and expands the
inspection area for cracking and corrosion to an area within five
inches of the fail-safe strap.
Revision 2 of this service bulletin adds an airplane that had been
removed from the Effectivity of Revision 1 of this service bulletin. In
addition, Revision 2 of this service bulletin adds procedures for a
related investigative action for certain crack findings during the
ultrasonic inspection specified in Revision 1 of this service bulletin.
The related investigative action involves an open-hole HFEC inspection
for cracking at the lower of three fastener holes common to the fail-
safe strap and the ``T'' fitting, and repair if necessary. The repair
includes various inspections (i.e., detailed, open-hole HFEC, and
surface HFEC) for cracking and corrosion of the ``T'' fitting and
adjacent structure; replacement of the ``T'' fitting with a new ``T''
fitting; repair of corrosion within specified limits; and replacement
of the fail-safe strap with a new strap, if necessary. The service
bulletin specifies to contact Boeing for certain repair and replacement
procedures. Repairing the fail-safe strap or replacing the fail-safe
strap with a strap having a revised edge configuration eliminates the
need for the repetitive inspections only on the side of the airplane on
which the corrective action is done.
For airplanes on which a fail-safe strap is replaced with a strap
that does not have a revised edge configuration, the service bulletin
describes procedures for detailed and surface HFEC inspections for
cracks and corrosion of the fail-safe strap, and an ultrasonic
inspection for cracks of the fail-safe strap.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Proposed AD Requirements
This proposed AD would retain all of the requirements of AD 2004-
19-06 R1. This proposed AD would expand the applicability statement of
the existing AD. This proposed AD would also require accomplishing the
actions specified in Revision 2 of the service information described
previously, except as discussed under ``Differences Between the
Proposed AD and the Service Information.''
Differences Between the Proposed AD and the Service Information
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Changes to Existing AD
We have added a new paragraph (d) to this proposed AD to provide
the Air Transport Association (ATA) of America subject code 53,
Fuselage. This code is added to make this proposed AD parallel with
other new AD actions. We have re-identified subsequent paragraphs
accordingly.
We have revised the existing AD to identify the legal name of the
manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
Since AD 2004-19-06 R1 was issued, the AD format has been revised,
and certain paragraphs have been rearranged. As a result, the
corresponding paragraph identifiers have changed in this proposed AD,
as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2004-19-06 R1 proposed AD
------------------------------------------------------------------------
paragraph (d). paragraph (e).
paragraph (e). paragraph (f).
paragraph (f). paragraph (g).
paragraph (g). paragraph (h).
------------------------------------------------------------------------
Costs of Compliance
We estimate that this proposed AD affects 390 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection for Model 767-200, - 2 work-hours x $85 $0 $170 per inspection $60,180 per
300, and -300F airplanes per hour = $170 per cycle.. inspection cycle.
(retained actions from existing inspection cycle.
AD).
New proposed inspections for all 2 work-hours x $85 $0 $170 per inspection $66,300 per
airplanes (new proposed action). per hour = $170 per cycle.. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of
aircraft that might need these repairs/replacements:
[[Page 10290]]
On-condition costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair or replacement, Groups 1-7, 295 work-hours x $85 Between $9,054 and Between $34,129 and
10, and 11 airplanes. per hour = $25,075. $15,837. $40,912.
Repair or replacement, Groups 8 and 9 297 work hours x $85 Between $32,593 and Between $57,838 and
airplanes. per hour = $25,245. $32,727. $57,972.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2004-19-06 R1, Amendment 39-14313 (70 FR 58000, October 5, 2005),
and adding the following new AD:
The Boeing Company: Docket No. FAA-2011-0044; Directorate Identifier
2010-NM-059-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 11,
2011.
Affected ADs
(b) This AD supersedes AD 2004-19-06 R1, Amendment 39-14313.
Applicability
(c) This AD applies to Model 767-200, -300, -300F, and -400ER
series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 767-53A0100, Revision 2, dated January
15, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 53, Fuselage.
Unsafe Condition
(e) This AD was prompted by additional reports of cracks in 51
fail-safe straps on 41 airplanes; we have also received a report of
a crack found in the ``T'' fitting that connects the fail-safe strap
to the outboard edge of the pressure deck. We are issuing this AD to
detect and correct fatigue cracking or corrosion of the fail-safe
straps and the ``T'' fittings, which could result in cracking of
adjacent structure and consequent reduced structural integrity of
the fuselage.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Requirements of AD 2004-19-06 R1, Amendment 39-14313: Inspections and
Follow-On/Corrective Actions
(g) For Model 767-200, -300, and -300F series airplanes having
line numbers 1 through 931 inclusive: Except as provided by
paragraph (h) of this AD, prior to the accumulation of 15,000 total
flight cycles, or within 3,000 flight cycles after November 1, 2004
(the effective date of AD 2004-19-06 R1, Amendment 39-14313),
whichever occurs later, perform a detailed inspection and eddy
current inspection to detect cracking or corrosion of the fail-safe
straps between the side fitting of the rear spar bulkhead at body
station (BS) 955 and the skin, per Figure 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 767-53A0100, dated
September 26, 2002; or Boeing Alert Service Bulletin 767-53A0100,
Revision 2, dated January 15, 2010. As of the effective date of this
AD, use only Revision 2 of Boeing Alert Service Bulletin 767-
53A0100. Doing the inspections required by paragraph (i) of this AD
terminates the requirements of this paragraph.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, 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. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(1) If no crack or corrosion is found, repeat the inspections
thereafter at intervals not to exceed 6,000 flight cycles or 36
months, whichever occurs first, until paragraph (i) of this AD is
done.
(2) If any crack or corrosion is found, before further flight,
repair per a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a method approved in
accordance with paragraph (o) of this AD.
(h) For airplanes identified in paragraph (g) of this AD on
which the fail-safe strap has been replaced before November 1, 2004:
Do the actions required by paragraph (g) of this AD within 12,000
flight cycles after accomplishing the replacement.
Note 2: Steps 2 and 8 of the Work Instructions of Boeing Alert
Service Bulletin 767-53A0100, dated September 26, 2002, refer
incorrectly to Boeing 767 Airplane Maintenance Manual (AMM) 32-00-20
for opening the MLG doors; the correct reference is Boeing 767 AMM
32-00-15, which is referred to in steps 3 and 7 of the Work
Instructions. Step 2 also should state ``Open Main Landing Gear
(MLG) doors'' instead of ``Open Main Landing Green (MLG) doors.''
New Requirements of This AD With Revised Service Information:
Repetitive Detailed and Eddy Current Inspections
(i) Prior to the accumulation of 15,000 total flight cycles, or
within 3,000 flight cycles after the effective date of this AD,
whichever
[[Page 10291]]
occurs later: Perform detailed and eddy current inspections to
detect cracking and/or corrosion of the fail-safe straps between the
side fitting of the rear spar bulkhead at BS 955 and the skin, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-53A0100, Revision 2, dated January 15, 2010. If
no crack or corrosion is found, repeat the inspections thereafter at
intervals not to exceed 6,000 flight cycles or 36 months, whichever
occurs first. Accomplishing the actions required by this paragraph
ends the requirements of paragraphs (g) and (g)(1) of this AD.
Repetitive Ultrasonic Inspections
(j) Prior to the accumulation of 15,000 total flight cycles, or
within 3,000 flight cycles after the effective date of this AD,
whichever occurs later: Do an ultrasonic inspection of the fail-safe
strap for cracking, and all applicable related investigative
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-53A0100, Revision 2, dated January
15, 2010. Do all applicable related investigative actions before
further flight. If no crack is found, repeat the inspection
thereafter at intervals not to exceed 6,000 flight cycles or 36
months, whichever occurs first.
Corrective Actions
(k) If any corrosion is found during any inspection required by
paragraph (i) of this AD: Before further flight, repair the
corrosion, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-53A0100, Revision 2, dated January
15, 2010.
(l) If any crack is found during any inspection required by
paragraph (i) or (j) of this AD: Before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-53A0100, Revision 2, dated January 15, 2010;
except where the service bulletin specifies to contact Boeing for
appropriate action, before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(o) of this AD. Accomplishing the fail-safe strap trim repair in
accordance with Boeing Alert Service Bulletin 767-53A0100, Revision
2, dated January 15, 2010, ends the repetitive inspections required
by paragraphs (i) and (j) of this AD only on the side of the
airplane where the repair was done. Replacing the fail-safe strap
with a replacement strap that has the revised edge configuration in
accordance with Boeing Alert Service Bulletin 767-53A0100, Revision
2, dated January 15, 2010, ends the repetitive inspections required
by paragraphs (i) and (j) of this AD only on the side of the
airplane where the replacement was done.
Post-Replacement Inspections
(m) For any replacement strap that does not have a revised edge
configuration, as specified in Boeing Alert Service Bulletin 767-
53A0100, Revision 2, dated January 15, 2010: Within 12,000 flight
cycles after doing the replacement, accomplish the inspections
required by paragraphs (i) and (j) of this AD. Repeat the
inspections thereafter at intervals not to exceed 6,000 flight
cycles or 36 months, whichever occurs first. Replacing the fail-safe
strap with a replacement strap that has the revised edge
configuration in accordance with Boeing Alert Service Bulletin 767-
53A0100, Revision 2, dated January 15, 2010, ends the repetitive
inspections required by paragraphs (i) and (j) of this AD only on
the side of the airplane where the replacement was done.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(n) Actions accomplished before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 767-53A0100, Revision
1, dated August 11, 2006, are considered acceptable for compliance
with the corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
Information may be e-mailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane and 14 CFR 25.571,
Amendment 45, and the approval must specifically refer to this AD.
(4) AMOCs approved for AD 2004-19-06 and AD 2004-19-06 R1 are
approved as AMOCs for paragraphs (g) and (h) of this AD, as
applicable.
Related Information
(p) For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: (425)
917-6577; fax: (425) 917-6590; e-mail: [email protected].
(q) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 206-
544-5000, extension 1; fax: 206-766-5680; e-mail:
[email protected]; Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 15, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-4200 Filed 2-23-11; 8:45 am]
BILLING CODE 4910-13-P