[Federal Register Volume 72, Number 169 (Friday, August 31, 2007)]
[Proposed Rules]
[Pages 50284-50288]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-17287]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29061; Directorate Identifier 2006-NM-243-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-
12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 
Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -
60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and 
-50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 
(MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-88 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain McDonnell Douglas airplanes. The 
existing AD currently requires an initial

[[Page 50285]]

general visual or dye penetrant inspection, repetitive dye penetrant 
inspections, and replacement, as necessary, of the rudder pedal 
bracket. The existing AD also requires, for certain airplanes, 
replacing the rudder pedal bracket assemblies with new, improved parts, 
which would terminate the repetitive inspections. This proposed AD 
would, for certain airplanes, reduce initial inspection thresholds, 
remove an inspection option, and lengthen the repetitive inspection 
intervals. This proposed AD results from reports of failures of the 
captain's rudder pedal brackets before reaching the initial inspection 
threshold identified in the existing AD. We are proposing this AD to 
prevent failure of the rudder pedal bracket assembly, which could 
result in the loss of rudder and braking control at either the 
captain's or first officer's position.

DATES: We must receive comments on this proposed AD by October 15, 
2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     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.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024) for service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5324; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2007-29061; Directorate Identifier 2006-NM-243-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or may 
can visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground floor of the West Building at the street address stated in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after the Docket Management System receives them.

Discussion

    On March 31, 2006, we issued AD 2006-07-25, amendment 39-14552 (71 
FR 18201, April 11, 2006), for certain McDonnell Douglas Model DC-8-11, 
DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-
8-43 airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-50, -
60, -60F, and -70 series airplanes; Model DC-9-10, -20, -30, -40, and -
50 series airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 
(MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. That 
AD requires an initial general visual or dye penetrant inspection, 
repetitive dye penetrant inspections, and replacement, as necessary, of 
the rudder pedal bracket. The existing AD also requires, for certain 
airplanes, replacing the rudder pedal bracket assemblies with new, 
improved parts, which would terminate the repetitive inspections. That 
AD resulted from a report of numerous cracked rudder pedal brackets 
found during inspections of certain affected airplanes. We issued that 
AD to prevent failure of the rudder pedal bracket assembly, which could 
result in the loss of rudder and braking control at either the 
captain's or first officer's position.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-07-25, two Model MD-80 operators have 
reported failures of the captain's rudder pedal brackets before 
reaching the initial inspection threshold of 40,000 total landings 
specified in AD 2006-07-25. One operator reported finding a crack in 
the first officer's rudder pedal bracket at 34,000 landings. Lab 
analysis of these parts verified that fatigue was the cause of the 
failure. Boeing re-evaluated the current inspection interval and 
determined that lowering the initial threshold to 25,000 total landings 
is necessary for operators of Model DC-9-81 (MD-81), DC-9-82 (MD-82), 
DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 
airplanes.
    Boeing also determined that the general visual inspection for 
cracks is no longer necessary because the eddy current and dye 
penetrant inspections are adequate for Model DC-9-10, -20, -30, -40, 
and -50 series airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-
83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. 
In addition, Boeing has lengthened the repetitive inspection interval 
for the eddy current and any applicable dye penetrant inspection (also 
called ``special detailed inspections'') for these airplanes from 
intervals not to exceed 2,500 landings to intervals not to exceed 3,000 
landings.

Clarification of Applicability

    We have also clarified the applicability to include Model DC-8-71F, 
DC-8-72F, and DC8-73F airplanes. These models were inadvertently 
omitted from Table 1, paragraph (c), ``Applicability,'' of AD 2006-07-
25. However, these models were included in the effectivity of McDonnell 
Douglas DC-8 Alert Service Bulletin A27-273, dated May 16, 1989, which 
we referred to in AD 2006-07-25 as a source for identifying airplanes 
affected by that AD.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC9-27A307, Revision 
7, dated August 29, 2006. We referred to an earlier revision of this 
same service bulletin (McDonnell Douglas DC-9 Alert

[[Page 50286]]

Service Bulletin A27-307, Revision 6, dated December 19, 1994) as the 
appropriate source of service information for doing certain actions in 
AD 2006-07-25.
    The actions in Boeing Alert Service Bulletin DC9-27A307, Revision 
7, are essentially the same as those in McDonnell Douglas DC-9 Alert 
Service Bulletin A27-307, Revision 6. However, Boeing Alert Service 
Bulletin DC9-27A307, Revision 7, revises certain inspection thresholds 
and intervals. Revision 7 also removes a general visual inspection for 
certain airplanes and, instead, specifies a special detailed 
inspection. The special detailed inspection consists of either doing an 
eddy current inspection for cracking of the rudder pedal bracket 
assemblies and, if any crack is found, doing a penetrant inspection for 
cracking; or doing the penetrant inspection for cracking of the rudder 
pedal bracket assemblies. Revision 7 includes a definition of a special 
detailed inspection.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2006-07-25 and would retain the requirements of the 
existing AD. This proposed AD would also, for certain airplanes, reduce 
certain initial inspection thresholds, remove an inspection option, and 
lengthen certain repetitive inspection intervals.

Explanation of Changes to Existing AD

    We have changed the parts cost for the replacement to reflect the 
cost information in the current Boeing service information.
    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.
    We have revised references to certain service information to more 
accurately reflect the reference as cited on the service information 
itself.
    We have added a new paragraph (f) titled ``Service Information and 
Airplane Categories'' to reduce the length of the references to both in 
the AD itself. We have re-identified the paragraphs accordingly, and 
revised this action to refer to the airplane categories rather than 
list the models individually. We have also removed Note 2 of the 
existing AD because the new paragraph (f) makes the contents of the 
note unnecessary.

Costs of Compliance

    There are about 1,840 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The replacements are 
applicable only to Model DC-9-10, -20, -30, -40, and -50 series 
airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and 
DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                       Work     Average labor                                                   Number of U.S.-
              Action                  hours     rate per hour          Parts            Cost per airplane     registered airplanes       Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
General visual inspection                   3             $80  None.................  $240, per inspection   250..................  $60,000, per
 (required by AD 2006-07-25).                                                          cycle.                                        inspection cycle.
Dye penetrant (special detailed)            5              80  None.................  $400, per inspection   946..................  $378,400, per
 inspection (required by AD 2006-                                                      cycle.                                        inspection cycle.
 07-25).
Replacements (required by AD 2006-          9              80  $9,466...............  $10,186..............  up to 946............  up to $9,635,956.
 07-25).
--------------------------------------------------------------------------------------------------------------------------------------------------------

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); 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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:

[[Page 50287]]

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14552 (71 FR 18201, April 11, 2006) and adding 
the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2007-29061; Directorate Identifier 
2006-NM-243-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
15, 2007.

Affected ADs

    (b) This AD supersedes AD 2006-07-25.

Applicability

    (c) This AD applies to the airplanes identified in Table 1 of 
this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
               McDonnell Douglas--                  As identified in--
------------------------------------------------------------------------
Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-   McDonnell Douglas DC-8
 32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43        Alert Service
 airplanes; Model DC-8-51, DC-8-52, DC-8-53, and   Bulletin A27-273,
 DC-8-55 airplanes; Model DC-8F-54 and DC-8F-55    Revision 5, dated
 airplanes; Model DC-8-61, DC-8-62, and DC-8-63    February 18, 1993.
 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-
 63F airplanes; Model DC-8-71, DC-8-72, and DC-8-
 73 airplanes; Model DC-8-71F, DC-8-72F, and DC-
 8-73F airplanes.
Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-   Boeing Alert Service
 15, and DC-9-15F airplanes; Model DC-9-21         Bulletin DC9-27A307,
 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-   Revision 7, dated
 9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and   August 29, 2006.
 DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41
 airplanes; Model DC-9-51 airplanes; Model DC-9-
 81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83),
 and DC-9-87 (MD-87) airplanes; and Model MD-88
 airplanes.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of failures of the captain's 
rudder pedal brackets before reaching the initial inspection 
threshold identified in AD 2006-07-25. We are issuing this AD to 
prevent failure of the rudder pedal bracket assembly, which could 
result in the loss of rudder and braking control at either the 
captain's or first officer's position.

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 Information and Airplane Categories

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the applicable service bulletin 
identified in Table 2 of this AD. The term ``airplane category,'' as 
used in this AD, means the category identified in Table 2 of this 
AD.

                              Table 2.--Service Information and Airplane Categories
----------------------------------------------------------------------------------------------------------------
                                                               Called
                       For Model--                            airplane          Use this service bulletin--
                                                             category--
----------------------------------------------------------------------------------------------------------------
(1) DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33,               1  McDonnell Douglas DC-8 Alert Service
 DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51,                    Bulletin A27-273, Revision 1, dated
 DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54                    May 16, 1989; or Revision 5, dated
 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-                  February 18, 1993.
 63 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F
 airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes.
(2) DC-8-71F, DC-8-72F, and DC-8-73F airplanes...........               2  .....................................
(3) DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-              3  McDonnell Douglas DC-9 Alert Service
 15F airplanes; Model DC-9-21 airplanes; Model DC-9-31,                     Bulletin A27-307, Revision 1, dated
 DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34,                     May 16, 1989; or Boeing Alert
 DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-                   Service Bulletin DC9-27A307,
 9-41 airplanes; Model DC-9-51 airplanes.                                   Revision 7, dated August 29, 2006
                                                                            (after the effective date of this
                                                                            AD, only Revision 7 may be used).
(4) DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83),                  4  .....................................
 and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes.
----------------------------------------------------------------------------------------------------------------

Requirements of AD 2006-07-25

Initial Inspection Threshold

    (g) For airplane categories 1, 3, and 4, prior to the 
accumulation of 40,000 total landings or within 30 days after July 
5, 1989 (the effective date of AD 89-14-02, amendment 39-6245, which 
was superseded by AD 2006-07-25), whichever occurs later: Perform 
either a general visual inspection, dye penetrant inspection, or 
special detailed inspection (eddy current with dye penetrant or just 
dye penetrant), as applicable, for cracking of the captain's and 
first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 
5616068, respectively, in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified in Table 2 
of this AD. After the effective date of this AD, only the special 
detailed inspection specified in Boeing Alert Service Bulletin DC9-
27A307, Revision 7, may be used for airplanes identified in Revision 
7. For airplane category 4: Do the inspection required by this 
paragraph until the inspection required by paragraph (j) of this AD 
is accomplished.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

    (1) If an initial general visual inspection is accomplished, and 
no crack is found, perform a dye penetrant inspection of the rudder 
pedal bracket assembly within 180 days after the general visual 
inspection, and

[[Page 50288]]

thereafter accomplish dye penetrant inspections at intervals not to 
exceed 12 months or 2,500 landings, whichever occurs earlier. For 
airplane categories 3 and 4, repeat at this interval until the 
inspection required by paragraph (k) of this AD is accomplished.
    (2) If an initial dye penetrant inspection is accomplished, and 
no crack is found, accomplish repetitive dye penetrant inspections 
at intervals not to exceed 12 months or 2,500 landings, whichever 
occurs earlier. For airplane categories 3 and 4, repeat at this 
interval until the inspection required by paragraph (k) of this AD 
is accomplished.
    (3) If an initial special detailed inspection is accomplished 
after the effective date of this AD, and no crack is found, repeat 
the inspection in accordance with paragraph (k) of this AD.

Corrective Action

    (h) Except as provided by paragraph (l) of this AD: If any crack 
is detected during any inspection required by paragraph (g) or (j) 
of this AD, before further flight, remove and replace the rudder 
pedal bracket assembly in accordance with the service bulletin. 
Prior to the accumulation of 40,000 total landings after replacement 
with the new part, resume the repetitive inspections in accordance 
with paragraph (g) or (k) of this AD, as applicable. Doing the 
action required by paragraph (l) of this AD terminates the 
requirements of this paragraph for airplane category 4.

Terminating Action for Certain Airplanes

    (i) For airplane categories 3 and 4: Do the actions in 
paragraphs (i)(1) and (i)(2) of this AD in accordance with the 
Accomplishment Instructions of the service bulletin.
    (1) Before the accumulation of 75,000 total landings on the 
captain's rudder pedal bracket assembly, P/N 5616067-501, or within 
60 months after May 16, 2006, whichever occurs later: Remove the 
rudder pedal bracket assembly and replace it with new, improved P/N 
5962903-501. Accomplishment of the replacement terminates the 
repetitive inspections of the captain's rudder pedal bracket 
assembly required by paragraphs (g), (h), (j), (k), and (l) of this 
AD.
    (2) Before the accumulation of 75,000 total landings on the 
first officer's rudder pedal bracket assembly, P/N 5616068-501, or 
within 60 months after May 16, 2006, whichever occurs later: Remove 
the rudder pedal bracket assembly and replace it with new, improved 
P/N 5962904-501. Accomplishment of the replacement terminates the 
repetitive inspections of the first officer's rudder pedal bracket 
assembly required by paragraphs (g), (h), (j), (k), and (l) of this 
AD.

New Requirements of This AD

Revised Initial Inspection at Reduced Threshold for Certain 
Airplanes

    (j) For airplane categories 2 and 4, at the applicable time 
specified in paragraph (j)(1), (j)(2) or (j)(3) of this AD: Do a 
special detailed inspection for cracking of the captain's and first 
officer's rudder pedal bracket, part numbers (P/N) 5616067 and 
5616068, respectively, in accordance with the service bulletin. 
Doing this inspection terminates the inspection requirements of 
paragraphs (g) and (h) of this AD for airplane category 4.
    (1) For category 2 airplanes: Before the accumulation of 40,000 
total landings or within 30 days after the effective date of this 
AD, whichever occurs later.
    (2) For category 4 airplanes that have accumulated fewer than 
25,000 total landings as of the effective date of this AD: Before 
the accumulation of 25,000 total landings, or within 3,000 landings 
after the effective date of this AD, whichever occurs later.
    (3) For category 4 airplanes that have accumulated 25,000 or 
more total landings as of the effective date of this AD, do the next 
inspection at the applicable time in paragraph (j)(3)(i) or 
(j)(3)(ii) of this AD.
    (i) For category 4 airplanes on which the corrective action 
specified in paragraph (h) of this AD has not been accomplished, do 
the inspection within 3,000 landings after the effective date of 
this AD.
    (ii) For category 4 airplanes on which the corrective action 
required by paragraph (h) of this AD has been accomplished, do the 
inspection at the earlier of the following: The next repetitive 
interval required by paragraph (h) of this AD; 40,000 total landings 
after doing the corrective action required by paragraph (h) of this 
AD; or 3,000 landings after the effective date of this AD.

Repetitive Inspections at Revised Interval for Certain Airplanes

    (k) For airplane categories 3 and 4: Repeat the special detailed 
inspection required by paragraph (g) or (j) of this AD thereafter at 
intervals not to exceed 3,000 landings. Doing the first repetitive 
inspection required by this paragraph terminates the repetitive 
inspection requirements of paragraph (g) of this AD for airplane 
categories 3 and 4.

Corrective Action Including Reduced Inspection Threshold for 
Certain Airplanes

    (l) For airplane category 4: If any crack is detected during any 
inspection required by paragraph (g), (j), or (k) of this AD: Before 
further flight, remove and replace the rudder pedal bracket assembly 
in accordance with the service bulletin. Before the accumulation of 
25,000 total landings after replacement with the new part, resume 
the repetitive inspections in accordance with paragraph (k) of this 
AD. Doing the action in this paragraph terminates the requirements 
of paragraph (h) of this AD for airplane category 4.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, FAA, has the authority to approve 
AMOCs for this AD, if requested in accordance with 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) AMOCs, approved previously in accordance with AD 2006-07-25, 
amendment 39-14552; and AD 89-14-02, amendment 39-6245; are approved 
as AMOCs for the corresponding requirements of this AD.

    Issued in Renton, Washington, on August 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-17287 Filed 8-30-07; 8:45 am]
BILLING CODE 4910-13-P