78-23-14 R1: Tow Release System
FAA order 78-23-14 R1 is an airworthiness directive in force since August 17, 1984. The FAA's subject line: Tow Release System. It names Let BLANIK L-13: about 38 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: other and general.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- BLANIK LIMITED
- Models
- Blanik L-13, Blanik L-13 AC
- On this site
- Let BLANIK L-13 38 registered
Dates and paperwork
- In force since
- August 17, 1984
- Docket
- Unknown
- Status
- Current
- The FAA's document
- Read the order on the FAA's site
The order itself the regulatory text, as published
Show the full text (2,224 characters)
78-23-14 R1 LET BLANIK: Amendment 38-3349 as amended by Amendment 39-4894. Applies to Model L-13 gliders, Serial Numbers 170101 through 174730, certificated in all categories.
Compliance is required as indicated, unless already accomplished.
To prevent tow release malfunction due to structural cracks at the attach point of the tow release system countershaft bracket, accomplish the following:
(a) Within the next 10 hours time in service after the effective date of this AD, inspect the No. 1 bulkhead for cracks at the attach points of the tow release system countershaft brackets in accordance with Let Mandatory Bulletin No. L13/047 dated January 11, 1978, and Note 2 in Bulletin No. L13/047 (Supplement), dated April 1, 1978, or an equivalent procedure approved by the Manager, Aircraft Certification Staff, Europe, Africa and Middle East Office.
(b) If cracks are found during inspection in accordance with paragraph (a) of this AD, before further flight:
(1) Where cracks do not exceed 6 mm in length, repair and reinforce the No. 1 bulkhead in accordance with paragraph A, "Reinforcement of bulkhead No. 1" of Let Mandatory Bulletin No. L13/047 dated January 11, 1978, and Bulletin L13/047 (Supplement) dated April 1, 1978, or equivalent approved by the Manager, Aircraft Certification Staff, Europe, Africa and Middle East Office; or,
(2) Where cracks exceed 6 mm in length, repair and reinforce the No. 1 bulkhead in accordance with the metal repair procedures, Section 3 of FAA Advisory Circular 43.13-1A, or equivalent approved by the Manager, Aircraft Certification Staff, Europe, Africa, and Middle East Office.
(c) If no cracks are found during the inspection required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, reinspect, repair, and reinforce the No. 1 bulkhead as follows:
(1) If no cracks have developed, in accordance with the method specified in paragraph (b)(1) ofthis AD; or
(2) If cracks have developed, in accordance with the applicable method specified in paragraph (b) of this AD.
Amendment 38-3349 became effective November 27, 1978.
This Amendment 39-4894 becomes effective August 17, 1984.
Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 7, 2026. Connections as data: /graph/directive/78-23-14 R1.json · aircraft systems.