78946 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations 

Actions Compliance Procedures 

(2) For Group 1 airplanes: If there is no overturn skid plate installed, then install overturn 

skid plate kit P/N 11411–1–502 or an FAAapproved equivalent part number.

Within the next 180 days after July 7, 2008 

(the effective date of AD 2008–11–17).

Follow Snow Engineering Co. Service Letter 

#97, revised November 7, 2007; or Snow 

Engineering Co. Service Letter #97, revised 

September 19, 2008. 

(3) For Group 2 airplanes: Install P/N 11411–1– 

501 modification kit.

Within the next 180 days after January 28, 

2009 (the effective date of this AD).

Follow Snow Engineering Co. Service Letter 

#97, revised September 19, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Fort Worth Airplane 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Andy McAnaul, 

Aerospace Engineer, ASW–150, FAA San 

Antonio MIDO–43, 10100 Reunion Pl., Ste. 

650, San Antonio, Texas 78216; telephone: 

(210) 308–3365; fax: (210) 308–3370. 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. 

Material Incorporated by Reference 

(h) You must use Snow Engineering Co. 

Service Letter #97, revised November 7, 

2007; or Snow Engineering Co. Service Letter 

#97, revised September 19, 2008, 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 

Snow Engineering Co. Service Letter #97, 

revised September 19, 2008, under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On July 7, 2008 (73 FR 31351, June 2, 

2008), the Director of the Federal Register 

approved the incorporation by reference of 

Snow Engineering Co. Service Letter #97, 

revised November 7, 2007. 

(3) For service information identified in 

this AD, contact Air Tractor Inc., P.O. Box 

485, Olney, Texas 76374; telephone: (940) 

564–5616; fax: (940) 564–5612; e-mail: 

airmail@airtractor.com; Internet: http:// 

www.airtractor.com. 

(4) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(5) You may also review copies of the 

service information incorporated by reference 

for this AD 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. 

Issued in Kansas City, Missouri, on 

December 9, 2008. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–29568 Filed 12–23–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0858; Directorate 

Identifier 2008–NM–054–AD; Amendment 

39–15773; AD 2008–26–07] 

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–8–50 Series 

Airplanes; Model DC–8F–54 and DC– 

8F–55 Airplanes; Model DC–8–60 

Series Airplanes; Model DC–8–60F 

Series Airplanes; Model DC–8–70 

Series Airplanes; and Model DC–8–70F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

McDonnell Douglas airplanes identified 

above. This AD requires repetitive 

inspections of the lower skin and 

stringers at stations Xw=408 and 

Xw=¥408, and corrective actions if 

necessary. This AD results from reports 

of cracks in the skins and stringers at 

the end fasteners common to the 

stringer end fittings at stations Xw= 

408 and Xw=¥408 wing splice joints. 

We are issuing this AD to detect and 

correct fatigue cracking in the skins and 

stringers at the end fasteners common to 

the stringer end fittings at certain station 

and wing splice joints, which could 

result in wing structure that might not 

sustain limit load, and consequent loss 

of structural integrity of the wing. 

DATES: This AD is effective January 28, 

2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 28, 2009. 

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); telephone 206–544–9990; fax 

206–766–5682; e-mail 

DDCS@boeing.com; Internet https:// 

www.myboeingfleet.com. 

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: Dara 

Albouyeh, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5222; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

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–8–50 series 

airplanes; Model DC–8F–54 and DC– 

8F–55 airplanes; Model DC–8–60 series 

airplanes; Model DC–8–60F series 

airplanes; Model DC–8–70 series 

airplanes; and Model DC–8–70F series 

airplanes. That NPRM was published in 

the Federal Register on August 12, 2008 

(73 FR 46823). That NPRM proposed to 

require repetitive inspections of the 

lower skin and stringers at stations 

Xw=408 and Xw=–408, and corrective 

actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received from 

the commenters. 


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Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations 78947 

Request To Review Proposed 

Compliance Time for Accuracy 

The Air Transport Association (ATA), 

on behalf of its member UPS, requests 

that we review the compliance time 

specified in the NPRM against Boeing 

Alert Service Bulletin DC8–57A102, 

dated February 12, 2008 (‘‘the service 

bulletin’’). UPS points out that the 

Relevant Service Information section of 

the NPRM specifies a compliance time 

of ‘‘Before the accumulation of 20,000 

total flight cycles, or within 1,500 flight 

cycles or 2 years after the date of the 

service bulletin, whichever occurs 

latest.’’ UPS further points out that the 

compliance time specified in the service 

bulletin is ‘‘Before the accumulation of 

20,000 total flight cycles, or within 

1,500 flight cycles or 2 years after the 

date of the service bulletin, whichever 

occurs first.’’ UPS prefers that the 

NPRM be revised to match the service 

bulletin. 

We do not agree to revise the 

compliance time specified in this final 

rule. However, we find that clarification 

is necessary because the Relevant 

Service Information section of the 

NPRM does not accurately reflect the 

compliance time specified in the service 

bulletin. 

It was our intent that the compliance 

time specified throughout the NPRM 

match the compliance time specified in 

the service bulletin. The Relevant 

Service Information section of the 

NPRM should have described the 

compliance time specified in the service 

bulletin as follows: ‘‘Whichever occurs 

later: (1) Before the accumulation of 

20,000 total flight cycles; or (2) within 

1,500 flight cycles or 2 years after the 

date of the service bulletin (whichever 

occurs first).’’ Although it is not clear in 

the NPRM that the grace period is the 

earlier of ‘‘1,500 flight cycles or 2 years 

* * *,’’ it is clear that the compliance 

time is the later of 20,000 total flight 

cycles or the grace period (1,500 flight 

cycles or 2 years), as specified in the 

service bulletin. 

Because paragraph (f) of the NPRM 

refers to paragraph 1.E., ‘‘Compliance,’’ 

of the service bulletin as the appropriate 

source of information for the 

compliance time for the proposed 

actions, our intent was clear that the 

proposed compliance time for this AD 

match the compliance time provided in 

the service bulletin. No change to this 

final rule is necessary in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 87 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspection .......................... 6 $80 $0 $480, per inspection cycle 87 $41,760, per inspection 

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 

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 

■ 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 FAA amends § 39.13 by adding 

the following new AD: 

2008–26–07 McDonnell Douglas: 

Amendment 39–15773. Docket No. 

FAA–2008–0858; Directorate Identifier 

2008–NM–054–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective January 28, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all 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, DC–8–43, DC–8–51, DC–8–52, DC– 

8–53, DC–8–55, DC–8F–54, DC–8F–55, DC– 

8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8– 

62F, DC–8–63F, DC–8–71, DC–8–72, DC–8– 

73, DC–8–71F, DC–8–72F, and DC–8–73F 

airplanes; certificated in any category. 


pwalker on PROD1PC71 with RULES
78948 Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations 

Unsafe Condition 

(d) This AD results from reports of cracks 

in the skins and stringers at the end fasteners 

common to the stringer end fittings at 

stations Xw=408 and Xw=¥408 wing splice 

joints. We are issuing this AD to detect and 

correct fatigue cracking in the skins and 

stringers at the end fasteners common to the 

stringer end fittings at certain station and 

wing splice joints, which could result in 

wing structure that might not sustain limit 

load, and consequent loss of structural 

integrity of the wing. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections and Corrective 

Actions 

(f) At the times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin DC8–57A102, dated February 12, 

2008 (‘‘the service bulletin’’), except as 

provided by paragraph (g) of this AD: Do the 

applicable inspections for fatigue cracking of 

the lower skin and stringers at stations 

Xw=408 and Xw=¥408, and do all 

applicable corrective actions, by 

accomplishing all applicable actions 

specified in the Accomplishment 

Instructions of the service bulletin, except as 

provided by paragraph (h) of this AD. Do all 

corrective actions before further flight, in 

accordance with the service bulletin. 

Thereafter, repeat the inspections at the 

applicable intervals specified in paragraph 

1.E. of the service bulletin. 

(g) Where Boeing Alert Service Bulletin 

DC8–57A102, dated February 12, 2008 (‘‘the 

service bulletin’’), specifies a compliance 

time after the date on the service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(h) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin DC8–57A102, dated 

February 12, 2008, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, ATTN: Dara 

Albouyeh, Aerospace Engineer, Airframe 

Branch, ANM–120L, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5222; fax (562) 

627–5210; 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, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(4) Accomplishing the requirements of this 

AD is an acceptable AMOC with the 

requirements of paragraph (b) of AD 93–01– 

15, amendment 39–8469, for those areas of 

principal structural element 57.08.037/038. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin DC8–57A102, dated February 12, 

2008, 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, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–0024); 

telephone 206–544–9990; fax 206–766–5682; 

e-mail DDCS@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the service 

information that is incorporated by reference 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information 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. 

Issued in Renton, Washington, on 

December 12, 2008. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–30265 Filed 12–23–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0977; Directorate 

Identifier 2008–NM–124–AD; Amendment 

39–15775; AD 2008–26–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2B19 

aircraft fuel system against the new fuel tank 

safety standards * * *. 

The assessment showed that insufficient 

electrical bonding between the refuel/defuel 

shutoff valves and the aircraft structure could 

occur due to the presence of a nonconductive gasket (Gask-O-Seal). In addition, 

it was also determined that the presence of 

an anodic coating on the shutoff valve 

electrical conduit connection fitting could 

affect electrical bonding. The above 

conditions, if not corrected, could result in 

arcing and potential ignition source inside 

the fuel tank during lightning strikes and 

consequent fuel tank explosion. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 28, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Rocco Viselli, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 


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