6578 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations 

and Van Buren Counties, TN, to include 

the entirety of each county. 

Comments on the interim rule were 

required to be received on or before 

December 24, 2007. We did not receive 

any comments. Therefore, for the 

reasons given in the interim rule, we are 

adopting the interim rule as a final rule. 

This action also affirms the 

information contained in the interim 

rule regarding Executive Order 12866 

and the Regulatory Flexibility Act, 

Executive Orders 12372 and 12988, and 

the Paperwork Reduction Act. 

Further, for this action, the Office of 

Management and Budget has waived its 

review under Executive Order 12866. 

List of Subjects in 7 CFR Part 301 

Agricultural commodities, Plant 

diseases and pests, Quarantine, 

Reporting and recordkeeping 

requirements, Transportation. 

PART 301—DOMESTIC QUARANTINE 

NOTICES 

■ Accordingly, we are adopting as a 

final rule, without change, the interim 

rule that amended 7 CFR part 301 and 

that was published at 72 FR 60533–

60537 on October 25, 2007. 

Done in Washington, DC, this 30th day of 

January 2008. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. E8–2048 Filed 2–4–08; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29061; Directorate 

Identifier 2006–NM–243–AD; Amendment 

39–15362; AD 2008–03–12] 

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. The existing AD 

currently 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 currently requires, for certain 

airplanes, replacing the rudder pedal 

bracket assemblies with new, improved 

parts, which would terminate the 

repetitive inspections. For certain 

airplanes, this new AD requires initial 

inspection at a reduced threshold, 

removes an inspection option, and 

lengthens the repetitive inspection 

intervals. This 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 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 

March 11, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 11, 2008. 

On May 16, 2006 (71 FR 18201, April 

11, 2006), the Director of the Federal 

Register approved the incorporation by 

reference of certain other publications 

listed in the AD. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Long Beach 

Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, 

Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 

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: 

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: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–07–25, amendment 

39–14552 (71 FR 18201, April 11, 2006). 

The existing AD applies to certain 

McDonnell Douglas airplanes. That 

NPRM was published in the Federal 

Register on August 31, 2007 (72 FR 

50284). That NPRM proposed to retain 

the requirements of AD 2006–07–25. 

That NPRM also, for certain airplanes, 

proposed to reduce certain initial 

inspection thresholds, remove an 

inspection option, and lengthen certain 

repetitive inspection intervals. 

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. 

Request To Clarify Repetitive 

Inspections 

Air Transport Association (ATA), on 

behalf of its member American Airlines, 

requests that we clarify paragraphs (h) 

and (l) of the NPRM. These paragraphs 

specify repetitive inspections to 

continue based on the part number of 

the replaced rudder pedal bracket 

assemblies in accordance with 

paragraph (g) or (k) of the NPRM. The 

commenters state that the referenced 

rudder pedal bracket assemblies should 

be clarified to indicate that repetitive 

inspections apply only to rudder pedal 

bracket assemblies that are of the same 

part number as the ones inspected. 

We agree with the request for the 

reasons stated. The intent of the 

replacement in paragraphs (h) and (l) of 

the NPRM is to replace the rudder pedal 

bracket assemblies with a part that has 

the same part number as the part 

inspected. Therefore, we have revised 

paragraph (h) and (l) of the AD to 

replace the words ‘‘new part’’ with 

‘‘same part number as the one 

inspected.’’

Request To Clarify Inspection Criteria 

in Paragraph (j) of the NPRM 

ATA, on behalf of its member ASTAR 

Air Cargo, requests that we clarify the 

inspection criteria in paragraph (j) of the 

NPRM. The commenters note that 

paragraph (j) of the NPRM specifies a 

special detailed inspection in 

accordance with McDonnell Douglas 


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DC–8 Alert Service Bulletin A27–273, 

Revision 1, dated May 16, 1989; or 

Revision 5, dated February 18, 1993. 

The commenters point out that the 

service bulletins do not have any 

inspection criteria listed. 

We agree with the commenters that 

the paragraph needs clarification. The 

intent of paragraph (j) of the AD is to 

specify a general visual inspection and 

penetrant inspection for Category 2 

airplanes in accordance with McDonnell 

Douglas DC–8 Alert Service Bulletin 

A27–273, Revision 1. Revision 1 of that 

service bulletin contains the inspection 

criteria. The intent of paragraph (j) was 

to specify a special detailed inspection 

for Category 4 airplanes in accordance 

with Boeing Alert Service Bulletin DC9–

27A307, Revision 7, dated August 29, 

2006. Revision 7 of that service bulletin 

contains the inspection criteria. We 

have revised paragraph (j) of the AD to 

clarify the requirements. 

Request To Clarify Compliance Time in 

Paragraph (j)(1) of the NPRM 

ATA, on behalf of its member ASTAR 

Air Cargo, also notes that paragraph 

(j)(1) of the NPRM specifies a 

compliance time of within 40,000 total 

landings or 30 days after the effective 

date of the AD, whichever occurs later. 

The commenters state that paragraph 

(j)(1) should refer instead to 40,000 total 

landings on the installed part. 

We agree with the commenters. 

McDonnell Douglas DC–8 Alert Service 

Bulletin A27–273, Revision 1, and 

Revision 5, specify a compliance time 

based on the accumulation of 40,000 

total landings on the bracket assembly. 

We have revised paragraph (j)(1) of the 

AD to specify that the compliance time 

is 40,000 total landings on the installed 

part. 

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 the economic burden 

on any operator nor increase the scope 

of the AD. 

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 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

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

General visual inspection (required by 

AD 2006–07–25).

3 $80 None ...... $240, per inspection cycle.250 .............. $60,000, per inspection cycle. 

Dye penetrant (special detailed) inspection (required by AD 2006–07– 

25).

5 80 None ...... $400, per inspection cycle.946 .............. $378,400, per inspection 

cycle. 

Replacements (required by AD 2006– 

07–25).

9 80 $9,466 .... $10,186 ................ up to 946 ..... up to $9,635,956. 

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 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14552 (71 

FR 18201, April 11, 2006) and by adding 

the following new airworthiness 

directive (AD): 

2008–03–12 McDonnell Douglas: 

Amendment 39–15362. Docket No. 

FAA–2007–29061; Directorate Identifier 

2006–NM–243–AD. 

Effective Date 

(a) This AD becomes effective March 11, 

2008. 


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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–8–32, 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; Model DC–8–71F, DC–8–72F, and DC–8–73F airplanes.

McDonnell Douglas DC–8 Alert Service Bulletin 

A27–273, Revision 5, dated February 18, 

1993. 

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.

Boeing Alert Service Bulletin DC9–27A307, Revision 7, dated August 29, 2006. 

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

For Model— Called airplane 

category— Use—

(1) 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.

1 McDonnell Douglas DC–8 Alert Service Bulletin 

A27–273, Revision 1, dated May 16, 1989; or 

Revision 5, dated February 18, 1993. 

(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–9–15F 

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.

3 McDonnell Douglas DC–9 Alert Service Bulletin 

A27–307, Revision 1, dated May 16, 1989; or 

Boeing Alert Service Bulletin DC9–27A307, 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), and DC–9–

87 (MD–87) airplanes; and Model MD–88 airplanes.

4 

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, 

dated August 29, 2006, 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 

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 


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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 a part that has the 

same number as the part inspected, 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 applicable service bulletin 

specified in Table 2 of this AD. 

(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 general visual 

and penetrant inspection (for airplane 

category 2), and a special detailed inspection 

(for airplane category 4), as applicable, to 

detect cracking of the captain’s and first 

officer’s rudder pedal bracket, part numbers 

(P/N) 5616067 and 5616068, respectively, in 

accordance with the applicable service 

bulletin specified in Table 2 of this AD. 

Procedures for the dye penetrant inspection 

for airplane category 2 are contained only in 

the Accomplishment Instructions of 

McDonnell Douglas DC–8 Alert Service 

Bulletin A27–273, Revision 1, dated May 16, 

1989. Procedures for the special detailed 

inspection are contained in Boeing Alert 

Service Bulletin DC9–27A307, Revision 7, 

dated August 29, 2006. Doing the applicable 

inspection required by this paragraph 

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 on the 

installed part, 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 with a part that has 

the same part number as the one inspected, 

in accordance with the applicable service 

bulletin specified in Table 2 of this AD. 

Before the accumulation of 25,000 total 

landings after replacement, 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. 

Material Incorporated by Reference 

(n) You must use the service information 

listed in Table 3 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 3.—ALL MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision 

level Date 

McDonnell Douglas DC–8 Alert Service Bulletin A27–273 ............................................................................. 1 May 16, 1989. 

McDonnell Douglas DC–8 Alert Service Bulletin A27–273 ............................................................................. 5 February 18, 1993. 

McDonnell Douglas DC–9 Alert Service Bulletin A27–307 ............................................................................. 1 May 16, 1989. 

Boeing Alert Service bulletin DC9-27A307 ..................................................................................................... 7 August 29, 2006. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

McDonnell Douglas DC–8 Alert Service 

Bulletin A27–273, Revision 5, dated February 

18, 1993; and Boeing Alert Service Bulletin 

DC9–27A307, Revision 7, dated August 29, 

2006; in accordance with 5 U.S.C. 552(a) and 

1 CFR part 51. 

(2) On May 16, 2006 (71 FR 18201, April 

11, 2006), the Director of the Federal Register 

approved the incorporation by reference of 

McDonnell Douglas DC–8 Alert Service 

Bulletin A27–273, Revision 1, dated May 16, 

1989; and McDonnell Douglas DC–9 Alert 

Service Bulletin A27–307, Revision 1, dated 

May 16, 1989. 

(3) 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 FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington; 


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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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

24, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–1813 Filed 2–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28956; Directorate 

Identifier 2007–CE–068–AD; Amendment 

39–15360; AD 2008–03–10] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 525, 525A, 

and 525B Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Models 525, 525A, and 525B airplanes. 

This AD requires you to inspect the 

lower wing skin structure, forward wing 

spar, lower fuselage skin, fairings, and 

the external fairing frames for corrosion; 

repair any damage found; apply a 

corrosion inhibitive sealant to the 

fuselage fairings before reinstalling; and 

disable the cockpit mounted pilot relief 

tube. This AD results from leaking of the 

cockpit mounted pilot relief tube, which 

caused corrosion of the airplane 

structure. We are issuing this AD to 

detect and correct any damage from 

corrosion of the airplane structure. 

Corrosion of the airplane structure 

could cause structural degradation and 

lead to structural failure of the airplane 

with consequent loss of control. 

DATES: This AD becomes effective on 

March 11, 2008. 

On March 11, 2008, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

Aircraft Company, Citation Marketing 

Division, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: 1–800–835–

4090; fax: 1–800–517–8500. 

To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590, or on the Internet at http:// 

www.regulations.gov. The docket 

number is FAA–2007–28956; 

Directorate Identifier 2007–CE–068–AD. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer,1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–

4155; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 22, 2007, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain Cessna Models 525, 525A, and 

525B airplanes. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on October 26, 2007 (72 FR 60790). The 

NPRM proposed to require you to 

inspect the lower wing skin structure, 

forward wing spar, lower fuselage skin, 

fairings, and the external fairing frames 

for corrosion; repair any damage found; 

apply a corrosion inhibitive sealant to 

the fuselage fairings before reinstalling; 

and disable the cockpit mounted pilot 

relief tube. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the proposal or on the determination of 

the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 261 

airplanes in the U.S. registry. 

We estimate the following costs to do 

the inspection: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

80 work-hours × $80 per hour = $6,400 ................................................... Not applicable .................................. $6,400 $1,670,400 

We have no way of determining the 

number of airplanes that may need 

repair or further inspection based on the 

results of the inspection, or the costs 

associated with such repair or 

inspection. 

We estimate the following costs to 

disable the cockpit mounted pilot relief 

tube: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

.5 work-hour × $80 per hour = $40 ........................................................... Not applicable .................................. $40 $10,440 

Cessna will provide warranty credit to 

the extent specified in Cessna Citation 

Service Bulletin SB525–53–20, dated 

April 30, 2007; Cessna Citation Service 

Bulletin SB525A–53–01, dated April 30, 

2007; Cessna Citation Service Bulletin 

SB525B–53–01, dated April 30, 2007; 

Cessna Citation Alert Service Letter 

ASL525–53–04, Revision 2, dated 

August 19, 2007; Cessna Citation Alert 

Service Letter ASL525A–53–05, 

Revision 2, dated July 25, 2007; and 

Cessna Citation Alert Service Letter 

ASL525B–53–02, Revision 2, dated July 

25, 2007. 

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 


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