[Federal Register Volume 71, Number 69 (Tuesday, April 11, 2006)]
[Rules and Regulations]
[Pages 18201-18205]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-3380]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20797; Directorate Identifier 2004-NM-256-AD; 
Amendment 39-14552; AD 2006-07-25]
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: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain McDonnell Douglas airplanes, as listed 
above. That AD currently requires an initial general visual or dye 
penetrant inspection, repetitive dye penetrant inspections, and 
replacement, as necessary, of the rudder pedal bracket. This new AD 
also requires, for certain airplanes, replacing the rudder pedal 
bracket assemblies with new, improved parts, which terminates the 
repetitive inspections. This AD results from a report of numerous 
cracked rudder pedal brackets found during inspections of certain 
affected airplanes. 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.

DATES: This AD becomes effective May 16, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 16, 2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    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 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:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 89-14-02, amendment 39-
6245 (54 FR 27156, June 28, 1989). The existing AD applies to 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; and Model DC-8-50, -60, -60F, -70, and -70F series 
airplanes (hereafter referred to as DC-8 airplanes). The existing AD 
also applies to McDonnell Douglas 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 
(hereafter referred to as DC-9/MD-80 airplanes). That NPRM was 
published in the Federal Register on April 5, 2005 (70 FR 17216). That 
NPRM proposed to continue to require an initial general visual or dye 
penetrant inspection, repetitive dye penetrant inspections, and 
replacement, as necessary, of the rudder pedal bracket. That NPRM also 
proposed to require, for certain airplanes, replacing the rudder pedal 
bracket assemblies with new, improved parts, which would terminate the 
repetitive inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

[[Page 18202]]

Request To Reference Previous Service Bulletins

    Boeing requests that we reference Revisions 4, 5, and 6 of 
McDonnell Douglas DC-9 Alert Service Bulletin A27-307 for accomplishing 
the actions in this AD. Revisions 4, 5, and 6 of the service bulletin 
were approved previously as alternative methods of compliance (AMOCs) 
for paragraphs A and B of AD 89-14-02, which correspond to paragraphs 
(f) and (g) of this AD. Therefore, we infer the commenter would like us 
to add references to Revisions 4 and 5 of the service bulletin to 
paragraph (h) of this AD.
    We agree to reference Revision 4, dated June 3, 1991, and Revision 
5, dated February 14, 1992, of McDonnell Douglas DC-9 Alert Service 
Bulletin A27-307 in paragraph (h) of this AD, since the procedures in 
those revisions are essentially the same as those in Revision 6. As a 
result, we have not retained paragraph (i) of the NPRM, Credit for 
Previous Service Bulletins, in this AD.

Request To Revise the Cost of Compliance

    Alaska Airlines requests that we increase the estimated cost of 
parts to $9,882. The commenter states that the captain's rudder pedal 
bracket assembly (part number (P/N) 5962903-501) costs $4,769, and that 
the first officer's rudder pedal bracket assembly (P/N 5962904-501) 
costs $5,113. The commenter also states that these are the current 
prices quoted by the manufacturer, and that the prices may be 
considerably higher when an airplane has accumulated 75,000 total 
flight cycles (the compliance time for the replacements).
    We agree. We have confirmed with Boeing that since issuance of 
McDonnell Douglas DC-9 Alert Service Bulletin A27-307, Revision 6, 
dated December 19, 1994, the cost of the parts has increased as quoted 
by the commenter. Therefore, we have revised the Estimated Costs table 
in this AD accordingly.

Request To Terminate AD 89-14-02

    Boeing also requests that we terminate AD 89-14-02 instead of 
supersede it. Boeing proposes that we revise paragraph (b) of the NPRM 
to state that first accomplishment of paragraphs (f)(1) and (f)(2) 
constitutes terminating action for the repetitive inspections of AD 89-
14-02. As justification, Boeing asserts that this change will make it 
easier for operators to track compliance.
    We do not agree to revise paragraph (b) of this AD. Since this AD 
supersedes AD 89-14-02, the requirements of this AD replace the 
requirements of that existing AD. After the effective date of this AD, 
operators would be required to show compliance with this AD, not AD 89-
14-02. Furthermore, we have carried over the repetitive inspections and 
compliance times from AD 89-14-02 into this AD because those 
inspections continue to be required until the terminating action in 
this AD is accomplished for certain airplanes. To revise this AD as the 
commenter proposes would necessitate revising the compliance times in 
paragraphs (f) and (g) of this AD to account for operators who are 
currently inspecting in accordance with AD 89-14-02. Therefore, no 
change to this AD is necessary in this regard.

Request To Address Defective Parts Manufacturer Approval (PMA) Parts

    The Modification and Repair Parts Association (MARPA) requests we 
revise the NPRM to cover possible defective PMA alternative parts, 
rather than just the parts identified in the NPRM, so that those 
defective PMA parts also are subject to the NPRM. MARPA states that 
there are existing PMA parts for the rudder pedal brackets. MARPA also 
states that PMA manufacturers are encouraged--and in some cases, 
required--to identify PMA parts by alternative designations.
    We concur with the MARPA's general request that, if we know that an 
unsafe condition also exists in PMA parts, the AD should address those 
parts, as well as the original parts. However, we are not aware of 
other PMA parts that are equivalent to the defective rudder pedal 
bracket assemblies. In the event PMA equivalent parts are identified, 
we will consider further rulemaking.
    The MARPA's remarks are timely in that the Transport Airplane 
Directorate currently is in the process of reviewing this issue as it 
applies to transport category airplanes. We acknowledge that there may 
be other ways of addressing this issue to ensure that unsafe PMA parts 
are identified and addressed. Once we have thoroughly examined all 
aspects of this issue, including input from industry, and have made a 
final determination, we will consider whether our policy regarding 
addressing PMA parts in ADs needs to be revised. We consider that to 
delay this AD action would be inappropriate, since we have determined 
that an unsafe condition exists and that replacement of certain parts 
must be accomplished to ensure continued safety. Therefore, no change 
has been made to this AD in this regard.

Request To Reference PMA Parts

    MARPA also requests that we revise language in the NPRM to permit 
installation of PMA equivalent parts. MARPA states that the mandated 
installation of a certain part number ``is at variance with FAR 
21.303,'' which permits the installation of other (PMA) parts.
    We infer that the commenter would like this AD to permit 
installation of any equivalent PMA parts so that it is not necessary 
for an operator to request approval of an alternative method of 
compliance (AMOC) in order to install an ``equivalent'' PMA part. 
Whether an alternative part is ``equivalent'' in adequately resolving 
the unsafe condition can only be determined on a case-by-case basis, 
based on a complete understanding of the unsafe condition. We are not 
currently aware of any such parts. Our policy is that, in order for 
operators to replace a part with one that is not specified in the AD, 
they must request an AMOC. This is necessary so that we can make a 
specific determination that an alternative part is or is not 
susceptible to the same unsafe condition.
    In response to the MARPA's statement regarding a ``variance with 
FAR 21.303,'' under which the FAA issues PMAs, this statement appears 
to reflect a misunderstanding of the relationship between ADs and the 
certification procedural regulations of part 21 of the Federal Aviation 
Regulations (14 CFR part 21). Those regulations, including section 
21.303 of the Federal Aviation Regulations (14 CFR 21.303), are 
intended to ensure that aeronautical products comply with the 
applicable airworthiness standards. But ADs are issued when, 
notwithstanding those procedures, we become aware of unsafe conditions 
in these products or parts. Therefore, an AD takes precedence over 
other design approvals when we identify an unsafe condition, and 
mandating installation of a certain part number in an AD is not at 
variance with section 21.303.
    The AD provides a means of compliance for operators to ensure that 
the identified unsafe condition is addressed appropriately. For an 
unsafe condition attributable to a part, the AD normally identifies the 
replacement parts necessary to obtain that compliance. As stated in 
section 39.7 of the Federal Aviation Regulations (14 CFR 39.7): 
``Anyone who operates a product that does not meet the requirements of 
an applicable airworthiness directive is in violation of this 
section.'' Unless an operator obtains approval for an AMOC, replacing a 
part

[[Page 18203]]

with one not specified by the AD would make the operator subject to an 
enforcement action and result in a civil penalty. No change to this AD 
is necessary in this regard.

Change To Certain Service Bulletin References

    We referenced McDonnell Douglas DC-8 Alert Service Bulletin A27-273 
and McDonnell Douglas DC-9 Alert Service Bulletin A27-307, both dated 
May 16, 1989, as applicable, as the appropriate source of service 
information for accomplishing the actions required by AD 89-14-02. 
However, we inadvertently omitted the revision level of those service 
bulletins in AD 89-14-02. We have corrected those references in 
paragraph (f) and Note 2 of this AD.

Clarification of AMOC Paragraph

    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.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
significantly the burden on any operator nor increase the scope of the 
AD.

Costs of Compliance

    There are about 2,025 airplanes of the affected design in the 
worldwide fleet. This AD affects about 1,381 airplanes of U.S. 
registry; about 250 of those airplanes are Model DC-8 airplanes and 
about 1,131 are Model DC-9/MD-80 airplanes. The new replacements of 
this AD are applicable only to Model DC-9/MD-80 airplanes. The 
following table provides the estimated costs for U.S. operators to 
comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                          Average                                 Number of
                                  Work     labor                                    U.S.-
             Action               hours  rate per    Parts   Cost per  airplane   registered      Fleet cost
                                           hour                                   airplanes
----------------------------------------------------------------------------------------------------------------
General visual inspection             3       $65      None  $195                      1,381  $269,295
 (required by AD 89-14-02).
Dye penetrant inspection              5        65      None  $325, per                 1,381  $448,825, per
 (required by AD 89-14-02).                                   inspection cycle                 inspection cycle
Replacements (new action)......       9        65    $9,882  $10,467                   1,131  $11,838,177
----------------------------------------------------------------------------------------------------------------

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 AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this 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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-6245 (54 FR 27156, June 28, 1989) and by adding 
the following new airworthiness directive (AD):

2006-07-25 McDonnell Douglas: Amendment 39-14552. Docket No. FAA-
2005-20797; Directorate Identifier 2004-NM-256-AD.

Effective Date

    (a) This AD becomes effective May 16, 2006.

Affected ADs

    (b) This AD supersedes AD 89-14-02.

Applicability

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

[[Page 18204]]



                                             Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
                     McDonnell Douglas                                        As identified in-
----------------------------------------------------------------------------------------------------------------
Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33,  McDonnell Douglas DC-8 Alert Service Bulletin A27-
 DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, DC-  273, dated May 16, 1989.
 8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 and
 DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63
 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.
Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9- McDonnell Douglas DC-9 Alert Service Bulletin Model
 15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-   A27-307, Revision 6, dated December 19, 1994.
 9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-
 34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41
 airplanes; Model DC-9-51 airplanes; 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 was prompted by a report of numerous cracked rudder 
pedal brackets found during inspections of certain affected 
airplanes. 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.

Requirements of AD 89-14-02

    (f) 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), 
whichever occurs later, perform either a general visual inspection 
or dye penetrant inspection for cracks of the captain's and first 
officer's rudder pedal bracket, part numbers (P/N) 5616067 and 
5616068, respectively, in accordance with McDonnell Douglas DC-8 
Alert Service Bulletin A27-273 (for 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-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-
54 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63 
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), or McDonnell Douglas DC-9 
Alert Service Bulletin A27-307 (for Model DC-9-11, DC-9-12, DC-9-13, 
DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; 
Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-
34, DC-9-34F, and 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), both Revision 1, both dated May 16, 1989, as 
applicable.

    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.''


    Note 2: McDonnell Douglas DC-8 Alert Service Bulletin A27-273 
and McDonnell Douglas DC-9 Alert Service Bulletin A27-307, both 
Revision 1, both dated May 16, 1989, are hereinafter referred to as 
ASB A27-273 and ASB A27-307, respectively.

    (1) If an initial general visual inspection is accomplished, and 
no cracks are found, perform a dye penetrant inspection of the 
rudder pedal bracket assembly within 180 days after the general 
visual inspection, and thereafter accomplish dye penetrant 
inspections at intervals not to exceed 12 months or 2,500 landings, 
whichever occurs earlier.
    (2) If an initial dye penetrant inspection is accomplished, and 
no cracks are found, accomplish repetitive dye penetrant inspections 
at intervals not to exceed 12 months or 2,500 landings, whichever 
occurs earlier.
    (g) If cracks are detected, prior to further flight, remove and 
replace the rudder pedal bracket assembly in accordance with ASB 
A27-273 or A27-307, as applicable. Prior to the accumulation of 
40,000 total landings after replacement with the new part, resume 
the repetitive inspections in accordance with paragraph (f) in this 
AD.

New Requirements of This AD

Terminating Action for Certain Airplanes

    (h) For McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-
14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model 
DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-
9-34F, and 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), DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes: 
Do the actions in paragraphs (h)(1) and (h)(2) of this AD in 
accordance with the Accomplishment Instructions of McDonnell Douglas 
DC-9 Alert Service Bulletin A27-307, Revision 4, dated June 3, 1991; 
Revision 5, dated February 14, 1992; or Revision 6, dated December 
19, 1994.
    (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 the effective date of this AD, 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 (f) and (g) 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 the effective date of this AD, 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 (f) 
and (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs, approved previously in accordance with AD 89-14-02, 
amendment 39-6245, are approved as AMOCs for the corresponding 
requirements of this AD.

Material Incorporated by Reference

    (j) You must use the applicable service information identified 
in Table 2 of this AD to perform the actions that are required by 
this AD, unless the AD specifies otherwise.

                                  Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                  Service bulletin                     Revision level                     Date
----------------------------------------------------------------------------------------------------------------
McDonnell Douglas DC-8 Alert Service Bulletin A27-                  1  May 16, 1989.
 273.

[[Page 18205]]

 
McDonnell Douglas DC-9 Alert Service Bulletin A27-                  1  May 16, 1989.
 307.
McDonnell Douglas DC-9 Alert Service Bulletin A27-                  4  June 3, 1991.
 307.
McDonnell Douglas DC-9 Alert Service Bulletin A27-                  5  February 14, 1992.
 307.
McDonnell Douglas DC-9 Alert Service Bulletin A27-                  6  December 19, 1994.
 307.
----------------------------------------------------------------------------------------------------------------

    McDonnell Douglas Alert Service Bulletin A27-307, Revision 6, 
dated December 19, 1994, contains the following effective pages:

 
----------------------------------------------------------------------------------------------------------------
                                                 Revision level
                  Page Number                    shown on page                  Date shown on page
----------------------------------------------------------------------------------------------------------------
1-24..........................................                6  December 19, 1994.
25-36.........................................                5  February 14, 1992.
----------------------------------------------------------------------------------------------------------------

    The Director of the Federal Register approved the incorporation 
by reference of these documents in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. 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 a copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on 
the Internet at http://dms.dot.gov; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-3380 Filed 4-10-06; 8:45 am]
BILLING CODE 4910-13-P