66296 Federal Register / Vol. 66, No. 247 / Wednesday, December 26, 2001 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–38–AD; Amendment

39–12529; AD 2001–24–12]

RIN 2120–AA64

Airworthiness Directives: Rolls-Royce

Corporation (formerly Allison Engine

Company) 250–C20 Series Turboshaft

and 250–B17 Series Turboprop

Engines, Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document makes a

correction to Airworthiness Directive

(AD) 2001–24–12 applicable to RollsRoyce Corporation (formerly Allison

Engine Company) 250–C20 series

turboshaft and 250–B17 series

turboprop engines, that was published

in the Federal Register on December 4,

2001 (66 FR 62915). The AD number

being superseded was inadvertently

omitted under the PART 39—

AIRWORTHINESS DIRECTIVES

amendatory instruction 2 in the heading

of the AD. This document corrects that

omission. In all other respects, the

original document remains the same.

EFFECTIVE DATE: December 19, 2001.

FOR FURTHER INFORMATION CONTACT: John

Tallarovic, Aerospace Engineer, Chicago

Aircraft Certification Office, FAA, Small

Airplane Directorate, 2300 East Devon

Avenue, Des Plaines, IL 60018;

telephone (847) 294–8180, fax (847)

294–7834.

SUPPLEMENTARY INFORMATION: A final

rule; request for comments

airworthiness directive applicable to

Rolls-Royce Corporation (formerly

Allison Engine Company) 250–C20

series turboshaft and 250–B17 series

turboprop engines was published in the

Federal Register on December 4, 2001

(66 FR 62915). The following correction

is needed:

§ 39.13 [Corrected]

On page 62916, in the first column,

under PART 39—AIRWORTHINESS

DIRECTIVES, amendatory instruction 2,

the heading of the AD is corrected to

read as follows:

2001–24–12 Rolls-Royce Corporation

(formerly Allison Engine Company):

Amendment 39–12529. Docket No. 2001-

NE–38-AD. Supersedes AD 2001–20–51.

Issued in Burlington, Massachusetts, on

December 14, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–31327 Filed 12–21–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–283–AD; Amendment

39–12568; AD 2001–26–04]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–8 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–8 series airplanes

that have been converted from a

passenger-to a cargo-carrying

(‘‘freighter’’) configuration, that

requires, among other actions,

modification of the main deck cargo

door structure and fuselage structure;

replacement of fasteners in the two

door-side hinge elements; modification

of the main deck cargo floor; and

installation of a main deck cargo 9g

crash barrier. The actions specified by

this AD are intended to prevent opening

of the cargo door while the airplane is

in flight, and consequent rapid

decompression of the airplane including

possible loss of flight control or severe

structural damage. These actions are

intended to address the identified

unsafe condition.

DATES: Effective January 30, 2002.

ADDRESSES: Information pertaining to

this AD may be examined at the Federal

Aviation Administration (FAA),

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington;

or at the FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

Michael E. O’Neil, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712–4137; telephone (562)

627–5320; fax (562) 627–5210.

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 McDonnell

Douglas Model DC–8 series airplanes

that have been converted from a

passenger-to a cargo-carrying

(‘‘freighter’’) configuration was

published in the Federal Register on

September 27, 2000 (65 FR 58203). That

action proposed to require, among other

actions, modification of the main deck

cargo door structure and fuselage

structure; replacement of fasteners in

the two door-side hinge elements;

modification of the main deck cargo

floor; and installation of a main deck

cargo 9g crash barrier.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request To Revise Compliance Times

One commenter requests that the

compliance times specified in paragraph

(b) of the proposed AD be revised from

‘‘Within 2 years or 2,000 flight cycles

after the effective date of this AD,

whichever occurs first’’ to ‘‘within 3

years or 4,000 flight cycles after the

effective date of this AD, whichever

occurs first.’’ The commenter contends

that if the inspection and evaluation

required by that paragraph reveals a

discrepancy, the corrective modification

will be extensive. The commenter states

that such an extension would allow

operators to correct discrepancies at one

maintenance visit, and thus, minimize

airplane downtime.

The FAA agrees. Since issuance of the

NPRM, we have gained a better

understanding of the design feature of

the original modification relative to the

vertical side restraint installation and

decompression venting. We have

determined that the structure is

sufficiently robust, and that

accomplishing the required inspection,

evaluation, and modification, if

necessary, required by paragraph (b) of

this AD ‘‘within 3 years or 4,000 flight

hours after the effective date of this AD,

whichever occurs first,’’ will provide an

acceptable level of safety. For the same

reasons, we also find that the 2-year

compliance time for the modification

required by paragraph (e) of this AD can

be extended to ‘‘within 3 years or 4,000

flight hours after the effective date of

this AD, whichever occurs first.’’

Therefore, we have revised the

compliance times of paragraphs (b) and

(e) of the final rule accordingly.

The same commenter requests that the

compliance time specified in paragraph

(f)(2) of the proposed AD be revised

from ‘‘Within 2 years or 2,000 flight