[Federal Register Volume 73, Number 191 (Wednesday, October 1, 2008)]
[Rules and Regulations]
[Pages 56960-56964]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-20091]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29227; Directorate Identifier 2007-NM-100-AD; 
Amendment 39-15664; AD 2008-18-07]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
300, 747-400, 747-400D, and 747SR series airplanes. For certain 
airplanes, this AD requires a material type inspection to determine if 
the lower forward corner reveal of the number 3 main entry doors (MEDs) 
is a casting. If the reveals are castings, this AD requires repetitive 
inspections of the reveals for cracking, and corrective action if 
necessary. If the reveals are not castings, this AD requires a detailed 
inspection of the reveals for a sharp edge and repetitive inspections 
of the reveals for cracking, and corrective action if necessary. For 
certain other airplanes, this AD requires only a detailed inspection of 
the reveals for a sharp edge and repetitive inspections of the reveals 
for cracking, and corrective action if necessary. For certain other 
airplanes, this AD requires repetitive inspections of the reveals for 
cracking only, and corrective action if necessary. This AD also allows 
a certain replacement as an optional action for the material type 
inspection for certain airplanes. This AD results from reports of 
cracking and/or a sharp edge in the lower forward corner reveal of the 
number 3 MEDs. We are issuing this AD to detect and correct fatigue 
cracking of the lower forward corner reveal of the number 3 MEDs, which 
could lead to the door escape slide departing the airplane when the 
door is opened and the slide is deployed, and consequent

[[Page 56961]]

injuries to passengers and crew using the door escape slide during an 
emergency evacuation.

DATES: This AD is effective November 5, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 5, 
2008.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.

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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (NPRM) to 
amend 14 CFR part 39 to include an airworthiness directive (AD) that 
would apply to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 
747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series 
airplanes. That supplemental NPRM was published in the Federal Register 
on May 22, 2008 (73 FR 29716). For certain airplanes, that supplemental 
NPRM proposed to require a material type inspection to determine if the 
lower forward corner reveal of the number 3 main entry doors (MEDs) is 
a casting. If the reveals are castings, that supplemental NPRM proposed 
to require repetitive inspections of the reveals for cracking, and 
corrective action if necessary. If the reveals are not castings, that 
supplemental NPRM proposed to require a detailed inspection of the 
reveals for a sharp edge and repetitive inspections of the reveals for 
cracking, and corrective action if necessary. For certain other 
airplanes, that supplemental NPRM proposed to require only a detailed 
inspection of the reveals for a sharp edge and repetitive inspections 
of the reveals for cracking, and corrective action if necessary. For 
certain other airplanes, that supplemental NPRM proposed to require 
repetitive inspections of the reveals for cracking only, and corrective 
action if necessary. That supplemental NPRM also proposed to allow a 
certain replacement as an optional action for the material type 
inspection for certain airplanes.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the two commenters.

Support for the Supplemental NPRM

    Boeing concurs with the supplemental NPRM.

Request To Revise Costs of Compliance

    Northwest Airlines (NWA) requests that we revise the Costs of 
Compliance section in the supplemental NPRM. NWA points out that Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007 (which we referred to in the supplemental NPRM as the 
appropriate source of service information for doing the actions) 
specifies 11 hours to perform the inspection. NWA also states that it 
plans 8 hours to perform the inspection per doorway or 16 hours to 
perform the inspection per airplane.
    We disagree with the request to revise the Cost of Compliance 
section. The 11 hours estimate specified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 1, includes time to open and 
close access. The four-hour estimate specified in this AD represents 
the time necessary to perform only the actions actually required by 
this AD. We recognize that, in doing the actions required by an AD, 
operators might incur incidental costs in addition to the direct costs. 
The cost analysis in AD rulemaking actions, however, typically does not 
include incidental costs such as the time required to gain access and 
close up, time necessary for planning, or time necessitated by other 
administrative actions. We have not changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Costs of Compliance

    There are about 715 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                            Number of
                                                      Average                                 U.S.-
                Action                  Work hours   labor rate      Cost per airplane      registered                     Fleet cost
                                                      per hour                              airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections..........................            4          $80  $320, per inspection              119  $38,080, per inspection cycle.
                                                                  cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a

[[Page 56962]]

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 this AD:
    (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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new AD:

2008-18-07 Boeing: Amendment 39-15664. Docket No. FAA-2007-29227; 
Directorate Identifier 2007-NM-100-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective November 5, 
2008.

Affected ADs

    (b) Certain requirements of this AD terminate certain 
requirements of AD 2007-12-11, amendment 39-15089.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR 
series airplanes, certificated in any category, as identified in 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1, 
dated February 13, 2007, except airplanes that have been converted 
to an all-cargo configuration. The requirements of this AD also 
become applicable at the time when a converted airplane operating in 
an all-cargo configuration is converted back to a passenger or 
passenger/cargo configuration.

Unsafe Condition

    (d) This AD results from reports of cracking and/or a sharp edge 
in the lower forward corner reveal of the number 3 main entry doors 
(MEDs). We are issuing this AD to detect and correct fatigue 
cracking of the lower forward corner reveal of the number 3 MEDs, 
which could lead to the door escape slide departing the airplane 
when the door is opened and the slide is deployed, and consequent 
injuries to passengers and crew using the door escape slide during 
an emergency evacuation.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007.

Actions for Group 3 Airplanes

    (g) For airplanes identified as Group 3 airplanes in the service 
bulletin: Before the accumulation of 10,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later, do a detailed inspection for cracking of the 
lower forward corner reveals in accordance with Part 8 of the 
service bulletin.
    (1) If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 6,000 flight cycles until a new or reworked 
two-piece reveal is installed in accordance with Part 2 of the 
service bulletin. No further action is required by this paragraph 
for that location only after the replacement.

    Note 1: For the purpose of this AD, a one-piece machined 
aluminum reveal may be reworked into a two-piece reveal in 
accordance with Part 7 of the service bulletin after it was verified 
to be crack free and without a sharp edge in accordance with Part 5 
of the service bulletin, or after it was confirmed to be crack free 
in accordance with Part 5 of the service bulletin and reworked to 
remove a sharp edge in accordance with Part 6 of the service 
bulletin.

    (2) If cracking is found, do the replacement specified in 
paragraph (g)(2)(i) or (g)(2)(ii) of this AD.
    (i) Before further flight, replace the reveal with a new or 
reworked two-piece reveal in accordance with Part 2 of the service 
bulletin. No further action is required by this paragraph for that 
location only after the replacement.
    (ii) Before further flight, replace the reveal with a new or 
reworked one-piece machined aluminum reveal without a sharp edge in 
accordance with Part 3 of the service bulletin. Before the 
accumulation of 10,000 flight cycles on the replacement reveal since 
new, do the inspection for cracking specified in Part 8 of the 
service bulletin and repeat the inspection thereafter at intervals 
not to exceed 6,000 flight cycles until a new or reworked two-piece 
reveal is installed in accordance with Part 2 of the service 
bulletin. If any cracking is found during any inspection required by 
this paragraph, before further flight, do the action specified in 
paragraph (g)(2) of this AD. No further action is required by this 
paragraph for that location only after the replacement with a two-
piece reveal.

    Note 2: For the purpose of this AD, a one-piece machined 
aluminum reveal with a sharp edge may be reworked into a one-piece 
machined aluminum reveal without a sharp edge in accordance with 
Part 6 of the service bulletin after it is confirmed to be crack 
free in accordance with Part 5 of the service bulletin. After the 
sharp edge is removed, the one-piece machined aluminum reveal 
without a sharp edge may be further reworked into a two-piece reveal 
in accordance with Part 7 of the service bulletin.

Actions for Group 2 Airplanes and Group 1, Configuration 2 Airplanes

    (h) For airplanes identified as Group 2 airplanes in the service 
bulletin: Before the accumulation of 1,500 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later, do the inspection specified in paragraph (j) 
of this AD.
    (i) For airplanes identified as Group 1, Configuration 2 
airplanes in the service bulletin: Within 1,500 flight cycles after 
the lower forward corner reveal was last replaced or 1,000 flight 
cycles after the effective date of this AD, whichever occurs later, 
do the inspection specified in paragraph (j) of this AD.
    (j) At the applicable times specified in paragraphs (h) and (i) 
of this AD: Do a detailed inspection of the lower forward corner 
reveals for cracking and a sharp edge in accordance with Part 5 of 
the service bulletin.
    (1) If no cracking and no sharp edge are found, before the 
accumulation of 10,000 flight cycles on the lower forward corner 
reveal since new, or within 6,000 flight cycles after doing the 
inspection required by paragraph (j) of this AD, whichever occurs 
later, do the detailed inspection for cracking in accordance with 
Part 8 of the service bulletin and inspect thereafter at intervals 
not to exceed 6,000 flight cycles, until a new or reworked two-piece 
reveal is installed in accordance with Part 2 of the service 
bulletin. If any cracking is found during any inspection required by 
this paragraph, before further flight, do the action specified in 
paragraph (j)(3) of this AD. No further action is required by this 
paragraph for that location only after the replacement with a two-
piece reveal.
    (2) If no cracking is found but a sharp edge is found, do the 
action specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
    (i) Before further flight, replace the lower forward corner 
reveal with a new or reworked two-piece reveal, in accordance with 
Part 2 of the service bulletin. No further action is required by 
this paragraph for that location only after the replacement.
    (ii) Before further flight, replace the reveal with a new or 
reworked one-piece machined aluminum reveal without a sharp edge, in 
accordance with Part 3 of the service

[[Page 56963]]

bulletin. Before the accumulation of 10,000 flight cycles on the 
replacement reveal since new, do the inspection for cracking in 
accordance with Part 8 of the service bulletin and inspect 
thereafter at intervals not to exceed 6,000 flight cycles, until a 
new or reworked two-piece reveal is installed in accordance with 
Part 2 of the service bulletin. If any cracking is found during any 
inspection required by this paragraph, before further flight, do the 
action required by paragraph (j)(3) of this AD. No further action is 
required by this paragraph for that location only after the 
replacement with a two-piece reveal.
    (3) If cracking is found, do the action specified in paragraph 
(j)(3)(i) or (j)(3)(ii) of this AD.
    (i) Before further flight, replace the reveal with a new or 
reworked two-piece reveal, in accordance with Part 2 of the service 
bulletin. No further action is required by this paragraph for that 
location only after the replacement.
    (ii) Before further flight, replace the lower forward corner 
reveal with a new or reworked one-piece machined aluminum reveal 
without a sharp edge, in accordance with Part 3 of the service 
bulletin. Before the accumulation of 10,000 flight cycles on the 
replacement reveal since new, do the inspection for cracking in 
accordance with Part 8 of the service bulletin and inspect 
thereafter at intervals not to exceed 6,000 flight cycles, until a 
new or reworked two-piece reveal is installed in accordance with 
Part 2 of the service bulletin. If any cracking is found during any 
inspection required by this paragraph, before further flight, do the 
action required by paragraph (j)(3) of this AD. No further action is 
required by this paragraph for that location only after the 
replacement with a two-piece reveal.

Actions for Group 1, Configuration 1 Airplanes

    (k) For airplanes identified as Group 1, Configuration 1 
airplanes in the service bulletin: Before the accumulation of 1,500 
total flight cycles, or within 1,000 flight cycles after the 
effective date of this AD, whichever occurs later, do a material 
type inspection to determine if the lower forward corner reveals are 
castings, in accordance with the service bulletin. As an alternative 
to the material type inspection, replacing a reveal with a new or 
reworked two-piece lower forward corner reveal in accordance with 
Part 2 of the service bulletin is terminating action for the 
requirements of this paragraph for that location only.
    (1) If the forward corner reveal is not a casting: Before 
further flight, do the actions specified in paragraph (j) of this AD 
except for the inspection for a sharp edge.
    (2) If the forward corner reveal is a casting: Before the 
accumulation of 7,000 total flight cycles, within 2,000 flight 
cycles after the effective date of this AD, or within 3,000 flight 
cycles since the forward corner reveal was inspected in accordance 
with Boeing Service Bulletin 747-53A2378, whichever is latest, do a 
detailed inspection for cracking of the lower forward corner reveal, 
in accordance with Part 1 of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007.
    (i) If no cracking is found: Repeat the inspection specified in 
paragraph (k)(2) of this AD thereafter at intervals not to exceed 
3,000 flight cycles until a new or reworked two-piece lower forward 
corner reveal is installed in accordance with Part 2 of the service 
bulletin. No further action is required by this paragraph for that 
location only after the replacement.
    (ii) If cracking is found: Do the actions specified in paragraph 
(k)(2)(ii)(A), (k)(2)(ii)(B), or (k)(2)(ii)(C) of this AD.
    (A) Before further flight, weld repair the reveal in accordance 
with Part 4 of the service bulletin. Repeat the inspection specified 
in paragraph (k)(2) of this AD thereafter at intervals not to exceed 
3,000 flight cycles until a new or reworked two-piece reveal is 
installed in accordance with Part 2 of the service bulletin. No 
further action is required by this paragraph for that location only 
after the replacement.
    (B) Before further flight, replace the reveal with a new or 
reworked two-piece reveal, in accordance with Part 2 of the service 
bulletin. No further action is required by this paragraph for that 
location only after the replacement.
    (C) Before further flight, replace the reveal with a new or 
reworked one-piece machined aluminum reveal without a sharp edge, in 
accordance with Part 3 of the service bulletin. Before the 
accumulation of 10,000 flight cycles on the replacement reveal since 
new, do the inspection for cracking in accordance with Part 8 of the 
service bulletin and inspect thereafter at intervals not to exceed 
6,000 flight cycles, until a new or reworked two-piece reveal is 
installed in accordance with Part 2 of the service bulletin. If any 
cracking is found during any inspection required by this paragraph, 
before further flight, do the action required by paragraph 
(k)(2)(ii)(B) or (k)(2)(ii)(C) of this AD. No further action is 
required by this paragraph for that location only after the 
replacement with a two-piece reveal.

Operator's Equivalent Procedure

    (l) Although Step 5 of Figure 8 of the service bulletin 
specifies that operators may accomplish the actions in accordance 
with ``an operator's equivalent procedure,'' this AD requires 
operators to accomplish Step 5 of Figure 8 in accordance with only 
the procedures specified in Boeing Standard Overhaul Practices 
Manual (SOPM) 20-20-02 as given in the service bulletin. An 
``operator's equivalent procedure'' may be used only if approved as 
an alternative method of compliance in accordance with paragraph (p) 
of this AD.

Compliance With AD 2007-12-11, Amendment 39-15089, for MED 3 Only

    (m) Accomplishment of the applicable repair required by this AD 
constitutes compliance with the repair of the lower forward corner 
casting (reveal) of the number 3 MEDs only, as required by paragraph 
(q)(2)(ii) of AD 2007-12-11 (which specifies the actions be done in 
accordance with Boeing Service Bulletin 747-53A2378, Revision 1, 
dated March 10, 1994; or Boeing Service Bulletin 747-53A2378, 
Revision 3, dated August 11, 2005). Accomplishment of the actions of 
this AD does not terminate the remaining requirements of AD 2007-12-
11.

Parts Installation

    (n) As of the effective date of this AD, no person may install a 
door lower forward corner reveal made of cast 356 aluminum on any 
airplane at a location specified by this AD.
    (o) As of the effective date of this AD, no person may install a 
door lower forward corner reveal made of machined 6061 aluminum on 
any airplane at a location specified by this AD, unless it has been 
confirmed/reworked to be without a sharp edge in accordance with the 
service bulletin.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6437; fax (425) 
917-6590; has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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 an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who 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 the approval must specifically refer to this 
AD.

Material Incorporated by Reference

    (q) You must use Boeing Special Attention Service Bulletin 747-
53-2460, Revision 1, dated February 13, 2007, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207.
    (3) You may review copies of the service information 
incorporated by reference 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.


[[Page 56964]]


    Issued in Renton, Washington, on August 20, 2008.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-20091 Filed 9-30-08; 8:45 am]
BILLING CODE 4910-13-P