Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6541

Effective Date 

(e) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on January 

30, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2574 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–333–AD; Amendment 

39–13464; AD 2004–03–20] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 1000, 2000, 3000, and 

4000 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Fokker Model F.28 

Mark 1000, 2000, 3000, and 4000 series 

airplanes, that requires repetitive 

general visual inspections, lubrication, 

and tests of the release mechanism for 

the service/emergency door; and 

corrective actions if necessary. This AD 

also provides an optional terminating 

action for the repetitive inspections and 

lubrication. This action is necessary to 

prevent failure of the release mechanism 

on the service/emergency door, which 

could result in the inability to open the 

service/emergency door during an 

emergency evacuation. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 17, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Fokker Services B.V., P.O. Box 

231, 2150 AE Nieuw-Vennep, the 

Netherlands. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., Suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Fokker 

Model F.28 Mark 1000, 2000, 3000, and 

4000 series airplanes was published in 

the Federal Register on December 5, 

2003 (68 FR 67981). That action 

proposed to require repetitive general 

visual inspections, lubrication, and tests 

of the release mechanism for the 

service/emergency door; and corrective 

actions if necessary. That action also 

proposed an optional terminating action 

for the repetitive inspections and 

lubrication. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

We have determined that air safety 

and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

We estimate that 6 airplanes of U.S. 

registry will be affected by this AD, that 

it will take approximately 15 work 

hours per airplane to accomplish the 

required actions, and that the average 

labor rate is $65 per work hour. Based 

on these figures, the cost impact of the 

AD on U.S. operators is estimated to be 

$5,850, or $975 per airplane, per 

inspection cycle. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–03–20 Fokker Services B.V:

Amendment 39–13464. Docket 2001–

NM–333–AD.

Applicability: Model F.28 Mark 1000, 

2000, 3000, and 4000 series airplanes; as 

listed in the effectivity of Fokker Service 

Bulletin F28/52–118, dated June 25, 2001; 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the release 

mechanism on the service/emergency door, 

which could result in the inability to open 

the service/emergency door during an 

emergency evacuation, accomplish the 

following: 

Inspection, Lubrication, Testing, and 

Corrective Actions 

(a) Within 12 months after the effective 

date of this AD: Do a general visual 

inspection (including measurement of the 

torque for the actuating mechanism torsion 

spring), lubricate, and test to verify proper 

6542 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

operation of the emergency release 

mechanism of the service/emergency door by 

accomplishing all of the actions specified in 

paragraphs A. through R. of the 

Accomplishment Instructions of Fokker 

Service Bulletin F28/52–118, dated June 25, 

2001.

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘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 enhance visual 

access to all exposed 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 no discrepant or corroded part is 

found during the inspection required by 

paragraph (a) of this AD: Repeat the actions 

specified in paragraph (a) of this AD 

thereafter at intervals not to exceed 1,500 

flight hours or 18 months, whichever occurs 

first. 

(2) If any discrepancy (including a torque 

value that exceeds the limits specified in the 

applicable service bulletin, an improperly 

installed part, or a damaged part) is found, 

or if a corroded part is found, during any 

inspection required by paragraph (a) of this 

AD: Before further flight, do the applicable 

corrective action in accordance with the 

Accomplishment Instructions of the service 

bulletin. Repeat the actions specified in 

paragraph (a) of this AD thereafter at 

intervals not to exceed 1,500 flight hours or 

18 months, whichever occurs first.

Optional Terminating Action and 

Concurrent Service Bulletin 

(b) Replacement of the Bowden cableoperated service/emergency door with a 

push-pull rod-operated service/emergency 

door, in accordance with Fokker Service 

Bulletin F28/52–89, dated October 31, 1983, 

constitutes terminating action only for the 

repetitive inspections and lubrication 

required by paragraph (a) of this AD. 

(c) For airplanes with serial numbers 11003 

to 11051 inclusive, 11991, and 11992: Prior 

to or concurrent with paragraph (b) of this 

AD, accomplish the modification specified in 

part VII of Fokker Service Bulletin F28/52–

55, Revision 1, dated February 28, 1977. 

Alternative Methods of Compliance 

(d) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(e) The actions shall be done in accordance 

with Fokker Service Bulletin F28/52–118, 

dated June 25, 2001. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Fokker Services B.V., P.O. Box 

231, 2150 AE Nieuw-Vennep, the 

Netherlands. Copies may be inspected at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the Office of the Federal Register, 800 North 

Capitol Street, NW., Suite 700, Washington, 

DC.

Note 2: The subject of this AD is addressed 

in Dutch airworthiness directive 2001–094, 

dated July 31, 2001.

Effective Date 

(f) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on January 

30, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2573 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–238–AD; Amendment 

39–13453; AD 2004–03–09] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200F, 747–200C, 

747–300, 747SR, and 747SP Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Boeing Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200F, 747–200C, 747–300, 747SR, 

and 747SP series airplanes. This AD 

requires repetitive inspections for 

discrepancies of the structure near and 

common to the upper chord and splice 

fittings of the rear spar of the wing, and 

repair if necessary. This AD also 

provides for an optional modification 

that, if accomplished, terminates the 

repetitive inspection requirement, but 

would necessitate eventual postmodification inspections. This action is 

necessary to find and fix fatigue 

cracking of structure near and common 

to the upper chord and splice fittings of 

the rear spar of the wing, which could 

result in loss of structural integrity of 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of March 17, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Nick 

Kusz, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6432; 

fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to all Boeing Model 

747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200F, 747–200C, 747–

300, 747SR, and 747SP series airplanes 

was published in the Federal Register

on June 18, 2003 (68 FR 36506). That 

action proposed to require repetitive 

inspections for discrepancies of the 

structure near and common to the upper 

chord and splice fittings of the rear spar 

of the wing, and repair if necessary. 

That action also proposed to provide for 

an optional modification that, if 

accomplished, would terminate the 

repetitive inspection requirement, but 

would necessitate eventual postmodification inspections. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

single comment received. 

Request To Change Paragraph (c) of the 

Proposed AD 

One commenter, the manufacturer, 

requests a change to paragraph (c) of the 

proposed AD to state, ‘‘If any cracking, 

corrosion, or damage is found * * *’’

rather than ‘‘If any cracking is found 

***’’. The commenter states that 

corrosion is often present in bolt holes 

vacated by alloy steel bolts, and that 

damage can occur during removal and 

installation of bolts. The commenter 

also requests that paragraph (c) be 

changed to reference ‘‘Part 3—

Inspection and Repair,’’ of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–57A2314, Revision 

1, dated January 9, 2003 (which is