Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Rules and Regulations 329

14 CFR Part 39

[Docket No. 94–NM–108–AD; Amendment

39–9109; AD 94–26–14]

Airworthiness Directives; British

Aerospace Model Viscount 744, 745D,

and 810 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model Viscount 744, 745D, and 810

series airplanes, that requires

inspections to detect cracks in the

chassis side bracing structure and in the

chassis top strut support intercostals

inside the wings, and replacement of

discrepant parts with new parts. This

proposal would also require inspection

of the intercostals to determine the

specification of the material, if

necessary, and replacement of

discrepant parts with new parts. This

amendment is prompted by a report of

cracking in the chassis top strut support

intercostal in the side bracing structure

inside the wing due to the effects of

metal fatigue. The actions specified by

this AD are intended to prevent such

fatigue-related cracking, which could

lead to the failure of the chassis side

bracing structure inside the wings and

consequent reduced structural integrity

of the chassis support structure.

DATES: Effective on February 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 3,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Regional

Aircraft Ltd., Engineering Support

Manager, Military Business Unit,

Chadderton Works, Greengate,

Middleton, Manchester M24 1SA,

England. 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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

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 British

Aerospace Model Viscount 744, 745D,

and 810 series airplanes was published

in the Federal Register on September 9,

1994 (59 FR 46596). That action

proposed to require repetitive detailed

visual inspections to detect cracks in the

chassis side bracing structure and in the

chassis top strut support intercostals of

the inner wings, and replacement of

discrepant parts with new parts. That

action also proposed to require an eddy

current inspection to determine the

specification of the material of the

intercostals, if necessary, and

replacement of discrepant parts with

new parts.

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.

The commenter supports the

proposed rule.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been added to this final rule to clarify

this requirement.

The FAA has recently reviewed the

figures it has used over the past several

years in calculating the economic

impact of AD activity. In order to

account for various inflationary costs in

the airline industry, the FAA has

determined that it is necessary to

increase the labor rate used in these

calculations from $55 per work hour to

$60 per work hour. The economic

impact information, below, has been

revised to reflect this increase in the

specified hourly labor rate.

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 25 Model

Viscount 744 and 745D series 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 $60 per work hour.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $22,500, or $900 per

airplane, per inspection cycle.

The FAA estimates that 4 Model

Viscount 810 series 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 $60 per work hour. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $3,600, or $900 per

airplane, per inspection cycle.

Based on the above figures, the total

cost impact of the actions proposed by

this AD on U.S. operators is estimated

to be $26,100, or $900 per airplane, per

inspection cycle.

The total 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 regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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.
330 Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Rules and Regulations

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

94–26–14 British Aerospace Regional

Aircraft Limited (Formerly British

Aerospace Commercial Aircraft Limited,

Vickers-Armstrongs Aircraft Limited):

Amendment 39–9109. Docket 94–NM–

108–AD.

Applicability: All Model Viscount 744,

745D, and 810 series airplanes, certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent reduced structural integrity of

the chassis, accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform a detailed visual

inspection to detect cracks in the chassis side

bracing structure and in the chassis top strut

support intercostals inside the wings

between stations 81 and 96, in accordance

with British Aerospace Viscount Preliminary

Technical Leaflet (PTL) 332, Issue 1, Disc 11

Doc.4, dated December 2, 1991 (for Model

Viscount 744 and 745D series airplanes); or

British Aerospace Viscount PTL 203, Issue 1,

Disc 11 Doc.2, dated December 2, 1991 (for

Model Viscount 810 series airplanes); as

applicable.

(1) If no cracking is detected in the chassis

side bracing structure, repeat the inspection

thereafter at intervals not to exceed 1,500

flight hours or 14 months, whichever occurs

first.

(2) If any cracking is detected in the chassis

side bracing structure, prior to further flight,

replace the cracked side of the bracing

structure with a new structure, in accordance

with the applicable PTL.

(3) If no cracking is detected in the chassis

top strut support intercostal, prior to further

flight, perform an eddy current inspection to

determine the specification of the material

(either L72 or L73) of the intercostals, in

accordance with the applicable PTL.

(i) If the material is manufactured from

L72, prior to further flight, replace the

chassis top strut support intercostal with a

new chassis top strut support intercostal, in

accordance with the applicable PTL.

(ii) If the material is manufactured from

L73, no further action is required by

paragraph (a)(3) of this AD.

(4) If cracking is detected in the chassis top

strut support intercostal, prior to further

flight, replace it with a new chassis top strut

support intercostal, in accordance with the

applicable PTL.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(d) The inspections and replacements shall

be done in accordance with British

Aerospace Viscount Preliminary Technical

Leaflet (PTL) 332, Issue 1, Disc 11 Doc.4,

dated December 2, 1991 (for Model Viscount

744 and 745D series airplanes); or British

Aerospace Viscount PTL 203, Issue 1, Disc 11

Doc.2, dated December 2, 1991 (for Model

Viscount 810 series airplanes); as applicable.

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 British Aerospace Regional Aircraft

Ltd., Engineering Support Manager, Military

Business Unit, Chadderton Works, Greengate,

Middleton, Manchester M24 1SA, England.

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.

(e) This amendment becomes effective on

February 3, 1995.

Issued in Renton, Washington, on

December 21, 1994.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–49 Filed 1–3–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–137–AD; Amendment

39–9107; AD 94–26–12]

Airworthiness Directives; Raytheon

Corporate Jets Model Hawker 800 and

1000 and Model DH/BH/HS/BAe 125

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon

Corporate Jets Model Hawker 800 and

1000 and Model DH/BH/HS/BAe 125

series airplanes, that requires

inspections to detect cracking of the

sidestay jack pivots of the main landing

gear, and replacement of the sidestay

jack pivot assemblies with new

assemblies. This amendment is

prompted by a report of fracturing of a

jack pivot, which resulted in the

inability of the main landing gear to

deploy. The actions specified by this AD

are intended to prevent a wheels-up

landing.

DATES: Effective February 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 3,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Corporate Jets, Inc., 3

Bishops Square Street, Albans Road

West, Hatfield, Hertfordshire, AL109NE,

United Kingdom. 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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal